VOLUME II ATTACHMENTS - LIGO DCC
311
1. VOLUME II ATTACHMENTS ATTACHMENT I P"* [ x-rGo- C9bo9b4'd-v STRUCTURAL CALCULATIONS TITLE I. LIGO VacuumEquipmentStructural Design Criteria II. BeamSplitter Chamber Finite Element Analysis of lJpperSection ASME Code Calculations for Upper Section FE Analysis of 1 in. Thick Flange for Bolt Preload FE Analysis of 1 in. ThickFlange for Bolt Preload & Pos' Pressure FE Analysis of 3/4 in Thick Flange Flange Designfor InternalPressure Design of Removable Work Floor I Design of Flange Welds Finite Element Analysis of LowerSection Design of 60 in Access Covers Design of Support Legs & Base Plates Temporary Coverfot 60 in Nozzle Nozzle to Shell Welds Lifting Lugs Shipping Loads BSC Deflections NASTRAN Buckling AnalYsis BSC Support Clevis Nozzle D AnalYsis For 200kg Force BSC PointLoads DOCUMENT REVISION NO. v049-1-066 0 v049-1-014 v049-l-015 v049-1-016 v049-1-017 v049-1-018 v049-l-019 v049-1-020 v049-1-021 va49-l-422 v049-1-023 v049-1-024 v049-l-025 v049-1-026 v049-l-027 v049-1-028 v049-1-029 v049-l-040 v049-1-069 v049-l-104 v049-l-l l l 0 0 0 0 0 0 0 I 0 0 0 0 0 0 0 I 0 0 0 0
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Transcript of VOLUME II ATTACHMENTS - LIGO DCC
1.
VOLUME II ATTACHMENTS
ATTACHMENT I P"* [x-rGo- C9bo9b4'd-v
STRUCTURAL CALCULATIONS
TITLE
I. LIGO Vacuum Equipment Structural DesignCriteria
II. Beam Splitter Chamber
Finite Element Analysis of lJpper SectionASME Code Calculations for Upper SectionFE Analysis of 1 in. Thick Flange for Bolt PreloadFE Analysis of 1 in. Thick Flange for Bolt Preload & Pos'
PressureFE Analysis of 3/4 in Thick FlangeFlange Design for Internal PressureDesign of Removable Work Floor
I Design of Flange WeldsFinite Element Analysis of Lower SectionDesign of 60 in Access CoversDesign of Support Legs & Base PlatesTemporary Cover fot 60 in NozzleNozzle to Shell WeldsLifting LugsShipping LoadsBSC DeflectionsNASTRAN Buckling AnalYsisBSC Support ClevisNozzle D AnalYsis For 200 kg ForceBSC Point Loads
DOCUMENT REVISIONNO.
v049-1-066 0
v049-1-014v049-l-015v049-1-016v049-1-017
v049-1-018v049-l-019v049-1-020v049-1-021va49-l-422v049-1-023v049-1-024v049-l-025v049-1-026v049-l-027v049-1-028v049-1-029v049-l-040v049-1-069v049-l-104v049-l-l l l
0000
000I0000000I0000
PROCESS ENGINEERING INC. S/N:8025064PAGE 2 RUN ID=XXl-l-111-
- r t ^ - . , - i - r - , { - r ^ \ . l o o r _ 1 9 9 3 ,- ! v t / I ! f Y r r u RtcA/Celestial Software =
CHECK GEOMETRY Versj-on 3.0 t2/3r/93
r 'a Lename=BSi -SUPPTit le =Beam Spl- iLter Chamber Support Structure
0 3 / 2 r / e 67 5 : 5 2 : 3 7
Shear Stress Fact.SSFy / SSFz
Pr. Bending Stress Recovery DisEancesN.1 a \ / - / c t r+ / ez - , / Cz+v l ' / ' l ' | ' ' p Ctors
l - 4 . 1 1 E + 0 02 2 . 0 0 E + 0 03 1 . 0 0 E + 0 04 2 . 0 0 E + 0 05 4 . 0 0 8 + 0 0
4 . l -1E+0 02 . 0 0 E + 0 0l - . 0 0 E + 0 02 . 0 0 8 + 0 04 . 0 0 8 + 0 0
4 . 3 8 E + 0 02 . 0 0 E + 0 0l - . 0 0 E + 0 04 . 0 0 8 + 0 04 . 0 0 E + 0 0
4 . 3 8 E + 0 02 . 0 0 E + 0 01 . O 0 E + 0 04 . 0 0 E + 0 04 . 0 0 E + 0 0
COORDINATES
Y - UOOrO .
8 . 1 0 8 - 0 11 . 9 2 E + 0 01 . 0 0 8 + 0 02 .448+003 . 7 9 8 + 0 0
z - uooro .
4 . 3 5 E + 0 02 . 3 1 8 + 0 01 . 0 0 E + 0 01 . 8 9 E + 0 02 . 3 3 8 + 0 0
1 . 9 2 E + 0 02 . 318+0 01 . 0 0 E + 0 03 . 4 3 E + 0 02 . 3 3 E + 0 0
Node
NODE
X-Coord.
*** WAIUIING _
11
34567o
1 01 1t2l -J
t 4L ]
1_71 8L 92 02 L
* * * NOdeS
0 . 0 0 0 0 0 8 + 0 00 . 0 0 0 0 0 E + 0 00 . 0 0 0 0 0 E + 0 08 . 4 0 0 0 0 8 + 0 18 . 4 0 0 0 0 E + 0 1I . 4 0 0 0 0 8 + 0 18 . 4 0 0 0 0 E + 0 18 . 4 0 0 0 0 E + 0 18 . 4 0 0 0 0 E + 0 10 . 0 0 0 0 0 8 + 0 00 . 0 0 0 0 0 8 + 0 00 . 0 0 0 0 0 8 + 0 0
- 4 . 2 0 0 0 0 E + 0 11 . 2 5 0 0 0 E + 0 24 . 2 0 0 0 0 E + 0 10 . 0 0 0 0 0 E + 0 08 . 4 0 0 0 0 E + 0 18 . 4 0 0 0 0 E + 0 1 -0 . 0 0 0 0 0 E + 0 00 . 0 0 0 0 0 E + 0 03 , 6 1 2 5 0 E + 0 1
2 0
0 . 0 0 0 0 0 E + 0 0 0 . 0 0 0 0 0 E + 0 01 . 8 0 0 0 0 8 + 0 1 0 . 0 0 0 0 0 8 + 0 04 . 4 0 0 0 0 E + 0 1 0 . 0 0 0 0 0 8 + 0 00 . 0 0 0 0 0 E + 0 0 0 . 0 0 0 0 0 E + 0 01 . 8 0 0 0 0 8 + 0 1 - 0 . 0 0 0 0 0 E + 0 04 . 4 0 0 0 0 8 + 0 1 0 . 0 0 0 0 0 8 + 0 00 . 0 0 0 0 0 E + 0 0 - 8 . 4 0 0 0 0 E + 0 11 . 8 0 0 0 0 E + 0 1 - 8 . 4 0 0 0 0 E + 0 1 -4 . 4 0 0 0 0 E + 0 1 - 8 . 4 0 0 0 0 E + 0 10 . 0 0 0 0 0 8 + 0 0 - 8 . 4 0 0 0 0 E + 0 11 . 8 0 0 0 0 8 + 0 1 - 8 . 4 0 0 0 0 E + 0 1 -4 . 4 0 0 0 0 8 + 0 1 - 8 . 4 0 0 0 0 E + 0 10 . 0 0 0 0 0 E + 0 0 - 4 . 2 0 0 0 0 8 + 0 10 . O 0 O 0 0 E + 0 0 - 4 . 2 0 0 0 0 E + 0 17 . 0 0 0 0 0 E + 0 1 - - 4 . 2 0 0 0 0 8 + 0 19 . 0 0 0 0 0 E + 0 0 0 . 0 0 0 0 0 8 + 0 09 . 0 0 0 0 0 E + 0 0 0 . 0 0 0 0 0 E + 0 09 . 0 0 0 0 0 8 + 0 0 - 8 . 4 0 0 0 0 8 + 0 19 . 0 0 0 0 0 E + 0 0 - 8 . 4 0 0 0 0 E + 0 10 . 0 0 0 0 0 E + 0 0 0 . 0 0 0 0 0 E + 0 07 . 0 0 0 0 0 E + 0 1 - 4 . 2 0 0 0 0 E + 0 1 -
a r e < = 0 . 0 0 0 1 a p a r t i n a l l 3 d i r s . * * *
BEAM CONNECTIVITY
Beam
d:Nodes
Err.1m / 'F.\ /
D 7 ^ h M . 1 -
Ref No NoPincodesr / J
RigidI .-T
Eincl Length BeamType
Revision No. 0Doc. No. V049-1424Pase lo of35
PROCESS ENGINEERTNG INC. S/N:8025054PAGE 3 RIIN ID=XX].1]-]-].
CHECK GEOMETRY
- b f I ename=H! ;eSUPP
Tit1e =Beam Spl i t ter Chamber Support
0 3 / 2 L / 9 5L O t > Z i J I
= C o p y r i g h t ( c ) 1 9 8 4 - 1 9 9 3 . Rl,cA/Celest ia l Software =
v e r s j - o n 3 . 0 1 2 / 3 1 / 9 3
Beam Nodes Prop MatNo From/ To / Ref No No
St ructure
Rigid End Offsets Lengthr / , J
Pincode sr / . r
1
345
789
1 01 1L 2-L.]
I 4.r, 15
r 1 6- a'7
1 8L 92 02 L
1_6 22 3
L T f
5 51 8 I
6 t t
1 9 1 11 1 L 2
2 5s 85 -L -L
L 1 2-1 I !
5 1 59 t_5
1 2 1 5-L -Lb
7 ] - 810 l_9L ] 2 : I
9 . 0 0 0 0 E + 0 02 . 6 0 0 0 E + A I9 . 0 0 0 0 8 + 0 02 . 5 0 0 0 8 + 0 1 -9 . 0 0 0 0 E + 0 02 . 6 0 0 0 8 + 0 19 . 0 0 0 0 8 + 0 02 . 5 0 0 0 E + 0 18 . 4 0 0 0 8 + 0 18 . 4 0 0 0 E + 0 18 . 4 0 0 0 E + 0 18 . 4 0 0 0 8 + 0 15 . 4 8 3 8 E + 0 1 -6 . 4 8 3 8 8 + 0 16 . 4 8 3 8 E + 0 1 -5 . 4 8 3 8 8 + 0 1 -9 . 0 0 0 0 E + 0 09 . 0 0 0 0 8 + 0 09 . 0 0 0 0 E + 0 09 . 0 0 0 0 E + 0 05 . 8 7 5 0 8 + 0 0
Beam. j t . "
;;;BeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeamBeam
l-313t4L 4!4L 4L J
l-3147
1 00000
I . J
1_41 4l_.J
0
55555555
3
3335555.1
11L111112
2
333
11L13
4 5
4 5
0 . 0 0 E + 0 0 0 . 0 0 E + 0 00 . 0 0 8 + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 E + 0 00 . 0 0 8 + 0 0 0 . 0 0 E + 0 00 . 0 0 E + 0 0 0 . 0 0 E + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 E + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 E + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 E + 0 0 0 . 0 0 E + 0 00 . 0 0 E + 0 0 0 . 0 0 8 + 0 00 . 0 0 8 + 0 0 0 . 0 0 8 + 0 00 . 0 0 8 + 0 0 0 . 0 0 E + 0 00 . 0 0 E + 0 0 0 . 0 0 E + 0 0
NodeNo
RESTRAIIVTS
G1oba1/LocaIRes traintDirect ions
147
1 0
G]-,OBAL XG].,OBA], XGLOBA]-,, XGLOBA], X
Y Z -Y Z -v z -v z -
NODAI CONNECTIVTTY
n. \1 - . . rnna. ' j -ad fn anr r e lement * * *
Revision No. 0Doc. No. V049-l{24Paee 1l cf 35
* * * WAI{NING - Node 1 3
PROCESS ENGINEERING INC. S/Nr802505APAGE 4 RUN TD=XX1111-1
CHECK GEOMETRY
I I -L ename =lJ: iUb U HYT i i - l c = R e ^ m q r i l i t r o r n h = m l l a - q r r h ^ ^ r r - q- -E rucEure
= C o p y r i g h t ( c ) 1 9 8 4 - 1 9 9 3 . RlcA/Celest ia l Software =
V C T S T O N J . U L 2 / 3 t / 9 3
E *.7 u. "r(.r-t o r
v 5 / z r / > ol o i > z i J l
P O A E
al a 'c )
*** WAI{NING _ Node L4*** WAIiNING - Node 20
connected to any element ***connected to any element **t(
nocnot
Revision No. 0Doc. No. V049-1424Pare 12 (If 35
pRocEss ENGTNEERTNG rNC. S /Nr8O25O5APAGH 5 RUN ID_
I M A G E= C o p y r i g h t ( c ) 1 9 8 4 - 1 9 9 3 .
RENWBER NODES Version 3.0
-F a -L ename =H5U5 U YYTit fe =Beam Spl i t ter Chamber Support Structure
NODE RENTTMBERING CROSS REFERENCE L]ST
0 3 / 2 1 - / 9 61 6 : 5 2 : . 3 7
c _ 2 r \
RLCA/Celest ia l Sof t .ware =
! 4 / 5 t / A 5
Was I s
I L ' J
O -L-L
1 1 1 316 1_7z J - o
Was Is
z r o
7 71 2 1 0] - 7 9
Was Is
- ' -L '
-L - ' I J
L d z
Was Is
9 57 4 2 01 9 I
Was Is
5 l-+1 0 3I ] L Z
2 0 2 7
Revision No. 0Doc. No. V049-1{24Paee 13 of 3 5
PROCESS ENGINEERING INC. S/N:802s05APAGE 5 Run ID=
ASSEMBLE STIFFNESS MATRIX Version 3.0
1,a Lename=llJSL-siUHPTit fe =Beam Spl i t ter Chamber SupporE Structure
0 3 / 2 t / 9 51 5 : 5 4 : 5 5
I M A G E S - 3 D = = = = = = = = == Copyr ight (c) 1984-1993. RlcA/Cefest ia l- Soft .ware =
i ) / - 1 1 / d 1
STIFFNESS ASSEMBLY SUMMARY
Number of Node Points 2INumber of Truss and Beam Elements. . . . . 2 lNumber of Plate El-ements 0Number of Spr ing Elements. 0Number of Solid Efements 0N u m b e r o f A x i s y m m e t r i c E 1 e m e n t s . . . . . . . 0Number of Nodes wi-th Rest.raints . . . . . . . 4N u m b e r o f E q u a t i o n s t o b e S o 1 v e d . . . . . . 9 5Number of Blocks in the Matr ix. 1
B L O C K I N F O R M A T I O N
BI,CKNO
BLCKNO
STZE SIZE(Byte )
B]-,CK SIZENo (Byre)
BLCK SIZENO (Byte)
1 4 2 0 8
Rsvision No. 0Doc. No. v049-1-024Pase 14 of35
PROCESS ENGINEERING INC. S/N:802505APAGE 7 Run ID=
= copy r igh t ( c ) 1984-1993 . RLCA/Cel-est ia l Software =
ASSEMBLE STIFFNESS MATRIX Version 3.0 1,2/31-/93
Fi- lename=BSCSUPPTit le =Beam Spl i tEer Chanber Support Structure
E Q U A T I O N
0 3 / 2 1 / 9 61 6 : 5 4 : 5 5
NODEWAS IS
N U M B E R
TRANSI.,AT I ONX Y Z
L I S T
ROTATIONX Y
Y 5 Y t t
u t t d I
80 81 -t4 1574 '75
55 5 "7? l
3 2 5 3
2 0 2 L1 1 L 2
i u t l
0 00 0
> z t 3
4 4 4 58 9
3 8 3 90 0
2 6 2 7
l_ 18 0 0 02 1 6 8 2 8 3 8 43 15 ' 76 77 784 4 0 0 05 1 4 7 0 7 t 7 25 t I 5 2 5 3 5 47 r 0 0 08 7 2 8 2 9 3 09 5 t6 t7 l _8
1 0 3 0 0 01 1 l - t 6 4 6 5 6 6L 2 1 0 4 6 4 7 4 813 1,9 0 0 01 _ 4 2 0 0 0 0L s L 2 5 8 5 9 5 01 5 t 7 8 8 8 9 9 0L 7 9 4 0 4 L 4 21 8 2 4 5 61 9 I 3 4 3 5 3 52 0 2 L 0 0 02 L 6 2 2 2 3 2 4
9 48 57 9- L J
t 5
5 5
3 1L 91 06 74 9
00
5 19 14 3
73 7
02 5
STIFFNESS SUMMARY IN
Minimum Diagonal St i f fness.Eq No of Minimum Diagonal. .Maximum Diagonal St i f fness.Eq No of Maximum Diagonal . .
BI,OCKS
. L 54l-D+0I2 8
.2597D+I I6 2
Revisiotr No. 0Doc. No. VO49-t{24Page l5 of35
PROCESS ENGINEERING INC.PAGE 8
S / N : 8 0 2 5 0 6 ' 4Run ID=
. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0
CONCEN|RATED LOADS
0 3 / 2 r / 9 5L 6 t 5 4 : 5 6
I M A G E S - 3 D = = = = = = = = == copy r igh t ( c ) 1984-1993 . RLcA/ce les t i -a1 So f tware =
SOL\G DISPI.,ACEMENTS Vers ion 3 .0 12 /31 - /93
-8 1-L ename =tJ.5UbU PHTiEle =Beam Spf it.ter Chamber Support Structure
] - , O A D C A S E 1MAXIMUM UNBAIJANCED ]-,OADS COMBINED WITH DEAD WT + EQ ( .055G)
GRAVITY LOADING
Node Fx Fy Fz Mx My
1 5 . 4 6 2 5 E + 0 52 L . 0 0 0 0 E + 0 0
- . 1 4 0 0 E + 0 5. 0 0 0 0 E + 0 0
. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0
. 2 9 4 4 E + 0 5 . 0 0 0 0 E + 0 0. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0. 0 0 0 0 E + 0 0 . 0 0 0 0 8 + 0 0
Revision No. 0Doc. No. V049-l{24Pese 16 of 35
REFERENCE TEMPERATURE = .00008+00
PROCESS ENGINEERING INC.PAGE 9
S / N : 8 0 2 5 0 5 ARun ID=
03/21,/95! 5 : 5 4 : 5 5
I M A G E S - 3 D = = = = = = = = == Copyr ight (c) 1984- l -993. RlcA/Celest ia l - Sof tware =
SOLVE DISPLACEMENTS v e r s t o n J . u 1 ) / 2 1 / o ' i .
! a Iename=tJSUSUPPTit le =Beam Spl- i tEer chamber Support Structure
MAXTMUM uNBALANCED "3J.o"3*rfi"3 ;t+r ps.lD wr + Ee(.056c)APPLIED ],OAD VECTOR
Node Fx Fy Fz Mx My
_L l
) 1
, 4 5 2 5 E + 0 5 - . 1 4 0 0 E + 0 5. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0
. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0
. 2 9 4 4 8 + 0 5 . 0 0 0 0 8 + 0 0. 0 0 0 0 E + 0 0. 0 0 0 0 8 + 0 0
. 0 0 0 0 E + 0 0
. 0 0 0 0 E + 0 0
Revision No. 0Doc. No. V049-l-024Pase '17
of 35
PROCESS ENGINEERING INC. S/N:8 02506APAGE t0 Run ID=
I M A G E= c o p y r i g h t ( c ) 1 9 8 4 - 1 9 9 3 .
0 3 / 2 r / e 6
s - 3 D = = = = = = 1 t : 5 4 r 5 6Rl,CA/Celestial Software =
V E I S A O N J . U 1 ) 1 1 1 / q 2 .SOLVE DISPI,ACEMENTS
! l - J-ename =l j t 'UbUYP
Title =Bean Spl-i.tter Charnlf,er Support Structure
L O A D C A S E 1MAXIMUM UNBAI,ANCED LOADS COMBINED WITH DEAD WT + EQ(.056G)
DISP].,ACEMENTS
NodeT r a n s l a t i o n sX Y Z
R o t a tY
l_.)
. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0
. 5 3 3 9 E - 0 1 . 1 2 5 0 E - 0 3 . 3 4 0 7 8 - 0 1 _
. 1 1 3 4 E + 0 0 . 1 3 5 3 8 - 0 3 . 6 3 3 5 8 - 0 1
. 0 0 0 0 8 + 0 0 . 0 0 0 0 8 + 0 0 . 0 0 0 0 E + 0 0
. 5 5 b y ! . i - u 1 - . 1 2 5 0 8 - 0 2 . 3 3 8 1 8 - 0 1
. 1 4 8 5 E + 0 0 - . 2 2 9 3 8 - 0 2 . 1 0 4 0 8 + 0 0
. 0 0 0 0 E + 0 0 . 0 0 0 0 8 + 0 0 . 0 0 0 0 8 + 0 0
. 5 0 5 9 E - 0 1 - . 3 7 4 ' 7 8 - 0 3 . 3 0 4 7 8 - 0 1
. 1 1 - l - 5 E + 0 0 - . 7 4 6 7 8 - 0 3 . 5 1 7 0 8 - 0 1 -
. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0 . 0 0 0 0 8 + 0 0
. 5 2 0 8 E - 0 1 - . 1 0 0 0 8 - 0 2 . 3 5 5 1 8 - 0 1
. 1 3 5 8 E + 0 0 . 1 5 8 3 E - 0 2 . 1 0 5 8 8 + 0 0
. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0
. 0 0 0 0 8 + 0 0 . 0 0 0 0 8 + 0 0 . 0 0 0 0 8 + 0 0
. 1 5 2 4 E + 0 0 - . a 3 6 4 8 - 0 2 . 9 7 0 3 E - 0 l -
. 2 8 2 1 8 - 0 1 . 5 2 5 0 E - 0 4 . 1 8 3 1 E - 0 1
. 2 8 3 2 E - 0 1 - . 6 2 4 9 E - 0 3 . 1 5 5 9 E - 0 1
. 2 6 6 2 E - 0 t - . 1 8 7 4 E - 0 3 . 1 5 5 7 E - 0 1
. 2 5 5 8 E - 0 1 . 5 0 0 1 E - 0 3 . 1 , 8 2 8 8 - 0 1
. 0 0 0 0 E + 0 0 . O O 0 0 E + 0 0 . 0 0 0 0 E + 0 0
. l - 5 2 4 E + 0 0 - . 5 9 4 4 8 - 0 2 . 9 7 8 5 8 - 0 1
. L t + z E - v z - . + + + - J E - u f - . 5 u z ) E - v z
. L 3 7 7 E - 0 2 - . 4 4 4 3 E - 0 5 - . 2 3 5 3 8 - 0 2- . 5 8 8 2 8 - 0 3 - . 1 3 1 9 E - 0 2
.28208E-04 - .31L28-02
.28208E-04 - .29028-02- . 5 7 0 3 E - 0 4 - . 2 9 8 1 E - 0 4
. 7 9 4 9 8 - 0 4 - . 2 8 6 6 8 - 0 2
. 7 9 4 9 8 - 0 4 - . 2 2 9 8 8 - 0 2
. 7 5 1 7 E - 0 3 - . 9 4 l - 1 8 - 0 3.2029E-02 .4685E- 04 - .29 ] -48 -02. 2 0 L 9 E - 0 2 . 4 6 8 5 E - 0 4 - . 2 5 7 5 8 - 0 2
- - L 9 7 9 E - 0 3 . 2 3 0 5 E - 0 3 - . 2 2 5 7 E - 0 3. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0. 0 0 0 0 E + 0 0 . 0 0 0 0 E + 0 0. 2 6 2 t 8 - 0 3 . 1 2 5 3 E - 0 3 - . 4 1 1 8 E - 0 3. l - 8 0 1 8 - 0 2 - . 4 4 4 3 8 - 0 5 - . 2 8 5 7 8 - 0 2
3
5
78
1 01 1r2_f.]
741 5_ L O
I 7l -81 92 02 7
. l - 0 9 0 E - 0 2
. 1 8 7 0 E - 0 2
. L9 648 - 02- . 5 / b _ L E - U - '
. L7 458- 02
. 1 1 5 1 E - 0 2
. L28 5E- 02
0 0 0 0 E + 0 00 0 0 0 E + 0 0
. 1 8 9 4 8 - 0 2
. l _ 5 9 5 E - 0 2. 2 8 2 0 8 - 0 4 - . 3 0 5 0 E - 0 2. 7 9 4 9 E - 0 4 - . 2 7 2 4 8 - 0 2
. 2 0 2 7 8 - 0 2 . 4 5 8 5 8 - 0 4 - . 2 8 5 5 8 - 0 2
. 0 0 0 0 E + 0 0- z o z r L - u 5
. 0 0 0 0 8 + 0 0 0 0 0 0 8 + 0 01 4 3 8 E - 0 3 - . 4 1 1 8 E - 0 3
Revision No. 0Doc. No. V049-1.024Pase lE of35
PROCESS ENGINEERING INC.rA\JE I Z
SOI.,VE BEA]"I LOADS/STRESSES
Fi l-ename =BSCSUPPTit le =Beam Spl- i t ter Chamber Support
i a / 1 i / a E
1 5 : 5 4 : 5 7
Structure
COMBINED WITH DEAD WT + EQ(.0s5G)
s / N : 8 0 2 5 0 5 ARun ID=
f M A G E S - 3 D = = = = = = = = == C o p y r l g h t ( c ) 1 9 8 4 - l - 9 9 3 . R L C A / C e l e s t i a l S o f t w a r e =
V e r s i o n 3 . 0 t 2 / 3 t / 9 3
r ^ ^ J ^ ^ ^ ^
c],oads NodeLloads Nodestress Node
FxAxi alAxi a1
Cornerl
Y - SNEAIY - S n e a rCorne r2
FzZ - ShearZ - ShearCorner3
MxTors ionTors ionCorne14
MyY-BendingY-Bending
Maximum
MzZ -Bendingz-Bending
Minimum
1:MAXIMUM UNBAL.,ANCE D LOADS
GLoadsGLoadsLL,oads
Stress
Stress
GL.,oads
LloadsLloadsStre s s
S t ress
cI,oadsGLoads
St ress
S t ress
LLoadsLI-.,oadsStress
Stress
* * *BEAI4. 1 0 5 0 E + 0 5 -
- . 1 0 5 0 8 + 0 5- . z z ) v E + v a
. 2 2 5 0 E + 0 5 -- . 3 0 0 7 8 + 0 4- . 5 ' 7 7 9 E + 0 4 -- . 3 0 0 7 8 + 0 4- . 1 0 9 5 E + 0 5 -
* * *BEAI{.7220E+04 -
- . 7 220E'+04- . l - 0 4 7 E + 0 5 -
. 1 0 4 7 E + 0 5- . 1 3 9 9 8 + 0 4 -
.2326E,+Q4 -- . 1 3 9 9 E + 0 4 -- . 7 8 3 0 E + 0 4 -
* * *BEjUvl- . 2 8 0 4 E + 0 5 -
. 2 8 0 4 8 + 0 5
. 4 4 3 0 E + 0 4 -- . 4 4 3 0 8 + 0 4
. 5 9 2 0 E + 0 3 -
. J - 5 L v E + U 4
. 5 9 2 0 E + 0 3 -
.14278+04* * *BEjUvl
- . 1 - 3 2 5 8 + 0 5 -. 1 3 2 5 E + 0 5. 1 7 5 9 E + 0 4 -
- . 1 7 5 9 E + 0 4. 2 3 5 1 8 + 0 3 -. 1 - 0 7 9 E + 0 5 -. 2 3 5 L 8 + 0 3 -.2094E+04
* * * BEI\]|[- . 9287E+04 -
N O .. l b z b t l + u l
- -L b.z b l1;+ u f,
. 5 0 2 7 E + 0 3
. 5 0 2 7 E + 0 3
.57LBE+02
. 5 0 1 5 8 + 0 4
. 57 788+Qz
. _ L _ L 4 J t l + U 5
N O ..4245E+04.4245E,+04.4468F,+04.44588+04.5971-E+03. 3 7 4 9 E + 0 4. 5 971E+03. 7 8 3 0 8 + 0 4
N O .. Z I O J E J + U )
. 27 638+ 03
. 482!E+04
. 4 821E+04
.64428+Q3
. 3 7 8 8 E + 0 4
.64428+03
. 5 9 5 5 E + 0 4N O .
. 9 0 4 3 E + 0 4
. 9 0 4 3 E + 0 4
. 1 4 5 5 8 + 0 5
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Revisioo No. 0Doc. No. V049-1{24Pa.se 20 of 35
I ooo.u'
IPROCESS ENGINEERING INC. S/N:802505APAG!,; TJ Run ID=
I M A G E= C o p y r i g h t ( c ) 1 9 8 4 - 1 9 9 3 .
0 3 / 2 7 / e 61 6 : 5 4 : 5 7
c _ 2 r \
RI-,CA/Ce l-est ia I Software =
SOLVE BEA}{ LOADS /STRESSES V e r s i o n 3 . 0 r z / s r / Y 3
r .I.Lename =lJSCS U PPTit1e -Beam Spl i tcer Chamber Support Structure
Load Case I:MAXIMUM UNBA]-,,ANCED I-.,OADS COMBINED WITH DEAD WT + EQ ( .055G)
Gloads NodeLl,oads NodeStress Node
FxAxi a1
Cornerl
FyY - ShearY- ShearCorner2
E zz - SnearZ - ShearCorner3
MxTorsi.onTorsionCorne14
My MzY-Bending Z-BendingY-Bending Z-Bending
Maximum Minimum
li*33:Stress
Stre6s
GLoadsGLoadsLl.,oadsLLoadsStre s s
Stress
cI-.,oadsLL.,oadsl-.,1-.,oadsS t ress
S t ress
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- . l a l + t i - U t -
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Rwision No. oDoc. Nc. V049-I424Pase 2l of 35
PROCESS ENGINEERING INC .
I M A G E= Copyr ight (c) 1984 - l -993 .
^ ^ / ^ . / ^ ?v J / 4 L / A O
1 6 : 5 4 : 5 7S _ 3 D
RlcA/celest ia l Software =
V e r s i o n 3 . 0 1 ) / 1 1 / o 2
s / N : 8 0 2 5 o 5 ARun ID=
SOLVE BEAM LOADS/STRESSES
ts a -Lename =IJsjclj U PPTit le =Beam Spf i t ter Chamber Support Structure
Load Case 1:MAXIMUM UNBA].,ANCED
Gloads Node Fx FyLloads Node Axial Y-ShearStress Node Axial Y-Shear
Cornerl Corner2
LOADS COMBINED WITH DEAD W T + E Q ( . 0 5 5 G )
My MzY-Bending Z-BendingY-Bending Z-Bending
Maximum Minimum
FzZ - Shearz - SnearCorner3
MxTors ionTors ionCorne14
LLoadsSt ress
S t res s
GLoadscloadsLLoadsLLoadsSt ress
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GLoadsI-.,L,oads
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S t ress
cl,oadsGI-,oadsI-.,L,oads
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cl-,oadsGLoadsLLoadsLI-,oadsStre s s
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. 2 0 1 4 E + 0 3 . 2 0 1 4 E + 0 3Rwision No. 0Doc. No. V049-1424P^ee 22 ctf 35
P R O C E S S E N G I N E E R I N G I N C . S / N : 8 0 2 5 0 5 APAG.Ej 15 Run ID=
I M A G E= c o p y r i g h E ( c ) l - 9 8 4 - 1 9 9 3 .
-F t -L ename =B:iCS UPP
Tits le =Beam Spl i t ter Chamber Support Slructure
n1 , / t 1 / qR
1 6 : 5 4 : 5 7c _ 2 n
RL,CA/Cel-estial- Software =
SOLVE BEAIVI ]-JOADS /STRESSES V e r s i o n 3 . 0 1 ) / 2 , i / q a ,
T ^ ^ l , - ^ ^ ^
Gloads NodeLtoads NodeStress Node
FXAxia I
Cornerl
FyY- ShearY- shearCorner2
FzZ - Shearz - snearCorner3
MxTors ionTors ionCorne14
I-:MAXIMUM IINBALANCET). LOADS COMBINED WrTH DEAD WT + EO(.056G)
My MzY-Bending Z-BendingY-Bending Z-Bending
Maximum Minimum
St ress
GLoadsGloadsLloadsL.,LoadsStrress
Stsress
GLoads
LLoadsSt ress
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Gloadscl,oadsI-,LoadsLloadsS t ress
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.3504E+05 .25748+04 . 14 65E- 1 - 0- . 3 5 0 4 E + 0 5 - . 2 5 7 4 E + 0 4 . 2 3 a 7 E + 0 5- . 5 8 8 5 E + 0 4 . 2 2 4 6 E + 0 4 . 9 7 7 0 E - L 3
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* * *BEAIvl NO. 19***. 1 0 5 0 8 + 0 5 - . 1 5 2 5 E + 0 5 - . 8 2 9 0 8 - 1 0
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* * *BEAIq NO. 20* * *- . 2 8 0 4 E + 0 5 - . 2 7 6 3 E + 0 3 - . 2 7 4 L E - I 0
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PROCESS ENGINEERING INC. S,/N:802505APAGE l-6 Run ID=
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v 5 / z ! / t o
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Revisior No. 0Doc. No. \1049-l{24P^!e 24 of 35
PROCESS ENGINEERING INC. S/N:8 02505APAUE Ll Run ID=
SOLVE BEAM LOADS/STRESSES
-b I -Lename=IJ! ' U:j UPP
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I-joad Case 1 : MAXIMUM LINBALANCED LOADS
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I M A G E S _ 3 D = = = = = = = = == copyr ight (c) I984-r9%. RlcA/Cefest iaf Softhrare =
MAXIMUM STRESS SUMMARY FORWITHIN SPECIFIED RANGE
BEAIVIS / TRUSSES1 - 2 I
El-ement Type Stress T)4)e
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Rwision No- 0Doc. No. V(M9-1-O24Pase 25 of 35
PROCESS ENGTNEERING INC. S/N:802506APAGE 18 Run ID=
SOLVE REACTIONS
Fi lename=BSCsuppTitfe =Beam Spf itt.er Chamber Suppor!
Load Case 1:MAXIMLM IINBAI,ANCED TOADS
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PROCESS SYSTEMS INTERNATIONAL. INC.WESTBOROUGH, MA
ENGINEERINGCALCULATIONS
NO: V049-1-025PAGE 1 OF 5
REV. DEO # DATE BY: CHECK TITLE: Design of Temporary Covers0 o 1 2 9 //t 7/9 L IZO e-., U b D
BY: R D- Ciafto DEPT..- 144
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. Design temporary shipping and test covers for 60.5 in nozzles in accordatrce withthe requirements of ASME Section VIII, Div. 1.
METHOD: Hand calculation to determine membrane and shear stresses.
ASSUMPTIONS:
IMUTS:l. Atmospheric pressure : 14.7 psi.2. Temperature = 70oF(s" /?'?/'r t')'
3 , T c n e = / o o o 3 D o t z t ^ j L B ' 7 ' < ' a e ; -
R-EFERENCES:1.I
ASME Boiler & Pressure Vessel Code, Section VIII, Div. 1, Pressure VesselsPpe . tJa . ,D ' /? - r -6cA
, l t t o /a t - 'u , - ,= t ' r 'P , IS - a , , , t : . ? E s ' . . . - ; ( p , + - - ; - + , , t ,
CALCULATIONS : (SEE ATTACHED)
CONCLUSIONS: The requirements of the ASME Code are met.
NOTES:
FILED:\F UEMPLATE\ENCFORMS\ENC,CALC
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PROCESS SYSTEMS INTERNATIONAL. INC.WESTBOROUGH,MA
ENGINEERINGCALCULATIONS
NO: V049-1-026PAGE i OF 3
REV. DEO# DATE BY: CHECK Beam Splitter Chamber - Evaluation of Nozzle toShell Weldso oo?,4 t z/Z/1f /z/o<_- AGR
BY:. )t . /) ,( t ,a.-r- c DEYI -:744
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. To evaiuate nozzle to shell fillet welds.
METHOD: Hand calculation using standard principles of mechaincs.
ASSUMPTIONS:
INPUTS: LIGO project sketches and drawings.
REFERENCES: ASME Boiler & Pressure Vessel Code, Section VIII, Division 1.2 - - . N o - / o / ? - / - o 6 6 , , / - / L D y ' ' a < ' r , " 4 E s o " ' , ! > - 4 , . , " 7 - " ' n 4 L
P , ? 3 , t r ' / C k t T t l L , & .
CALCULATIONS : (SEE ATTACIIED)
CONCLUSIONS: Nozde welds are acceptable.
NOTES:
o o o
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.OPROCESS SYSTEMS INTERNATIONAL, INC,
WESTBOROUGITMAENGINEERINGCAICULATIONS
NO: V049-1-027PAGE 1 OF 6
REV. DEO # DATE BY: CHECK Beam Splitter Chamber - Vessel Lifting Devices0 oo24 l TJC/t) /< rlca_ ND?)
BY: I( 2 -( )" -z -t? . DF.PT-: 7,14
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. To design lifting lugs and evaluate leg shesses when BSC is lifted and rotated to & froma horizontal position.
METHOD: Hand calculation using standard stress analysis method.
ASSUMPTTONS:
INPUTS: l.2.3 .
LIGO project skteches and drawings.Yerticalln o"'<agceleration = 19.D c e . N " , y ' O q f - / ' o 6
17"17 le -orA/'. PS: t s. 'J
6 t L t L ' 2 y ' . z e
U t t i
{i t-e;.- ,&. t -c t
Ea>sz r?, ,
REFERENCES:
CALCULATIONS : (SEE ATTACHED)
CONCLUSIONS: Lug & weld sftesses are acceptable. Stresses in support legs and shell are acceptable.
NOTES: A spreader beam should be used for the lift.
FTLED:UITEMS$ETE{GTORT'ts\ENC'q{C
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PROCESS SYSTEMS INTERNATIONAL, INC.WESTBOROUGH.MA
ENGINEERINGCALCULATIONS
NO: V049-1-028PAGE 1 OF 8
REV. DEO # DATE BY: CHECK Beam Splitter Chamber - Shipping Loadsz//? o /7 t f2 /,) U l^-fET5
RY R D Ciatlo DEPT.:744
PROJECT: LIGO Vacuum Equipment PROJECTNO: Vs9049
PURPOSE:. To waluate the BSC shell for loads imposed during shipping.
METHOD: The IMAGES finite elernent computer program is used to analyze shell stresses.
ASSUMPTIONS: It is assumed that the BSC will be shipped with its long axis in a horizontal position.Also, it is assumed that the vessel will be supported by 2 wood saddles during shipping
INPUTS: Vert shock accel: 1gHorizontal shock accel. = .59Internal Vacuum Pressure = -14.7 psi
REFERENCES: I IMAGES 3D, Version 3.0, R.L. Cloud & Associates. 2. Doc. No. V049-l-066, LIGO Vacuum Equipment, Structural Design Crireria
CALCULATIONS: (SEE ATTACT{ED)
CONCLUSIONS. Shell stresses that result from shipping loads are low. The vess€l can withstand ashock of 5Gs or mor€ without damage to the shell.
NOTES: The computer file name is BSC-SHIP.
t
I
PROCESS SYSTEMS INTERNATIONAL, INC.WESTBOROUGH,MA
ENGINEERINGCALCULATIONS
NO: V049-l-028PAGE I OF 7
REV. DEO # DATE BY: CIMCK Beam Splitter Chamber - Shipping Loads0 _at'. 8 n/4/9j /LDa_ L ttt
BY: iZ .,2 . Q ..a r. .s DEPT.:'144
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. To evaluate the BSC shell for loads imposed during shipping.
METTIOD: The IMAGES finite element computer prognm is used to analyze shell stesses.
ASSUMPTIONS: It is assumed that the BSC will be shipped with its long axis in a horizontal position.Also, it is assumed that the vessei will be supported by 2 wood saddles during shipping.
INPUTS: Vert shock accel: lgHorizontal shock accel. : .5s
REFERENCES: IMAGES 3D, Version 3.0, R.L. Cloud & Associates
CALCLTLATIONS : (SEE ATTACffiD)
CONCLUSIONS: Shell stresses that result from shipping loads are low. 7l".'= t/4 sr 4 Ll o o L ' t o , t 1 4 ! 4 / T . . 5 ' 2 4 € / < . 7 { . , i ! , : . ' e 4 - ? ' . ' 4 A / e s ' � t r ' / , t z t 6 t
NOTES: The computer file name is BSC-SHIP. *-t
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PROCESS SYSTEMS INTERNATIONAL. INC. ENGINEERINGCALCT'LATIONS
NO: V049-l{29WESTBOROI,rcILMA PAGE 1 OF 5
REV. DEO# DATE BY: CHECK TITLE: Beam Spliuer Chamber - Deflectionso alot4 trt6t9\ RIX:
n'r77 *.ntq6 P A . , - - uTDA
RY R D {lirtfn NFPT . ?44
PROJECT: IJGO Vaanum Equipment PROJECTNO: v59A49
PURPOSE: Compute estinated deflections at Beam Splitter 60.5 in Nozzles for vacuum loads.
METHOD: Combine shell deflections with suppgrt deflections to obtain mrxirnrm estimated d€flectionsfi pofts.
ASSIIMPfiONS: Bellows deflects with negligible force.
IMUTS: LI@ project drawing VM94-001 - Beam Splitter Chamber.LIGO prqiect diawing V049-5-001 ' Equipment Anangemert - Comer Station - WashingtonCalc. No. V049-1-066, Strucrural Design CriteriaCalc. No. V049-1-022, BSC, FE Analysis oflower SectionCalc. No. V049-l-024, BSC. Desis of Support l€gs and Base Plates
REFERENCES: SeEINPUTS
CALCULATIONS : (SEE ATIACHED)
CONCLUSIONS:
NOTES: The basis for the Rev. 1 deflections is the final support structurc.
Revision No. IDoc. No. V049-1429Page I of5
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ENGINEERINGCALCULATIONS
NO: V049-1-040PAGE I OF 7
REV. DEO # DATE BY: CHECK TITLE: Buckling Analysis of Beam Splitter Chamber0 1 t t z t l/z't/f,r 4F< /</) c__
BY: Kvle Manini lJF.Vf : 744
PROJECT: LIGO Vacuum Equipment PROJECT NO: V59049
PURPOSE:. Evaluate the beam splitter chamber (BSC) for buckling modes.
METHOD: Finite element method and hand calculation.
ASSUMPTIONS: See attached.
INPUTS: LIGO project drawings and sketches.
REFERENCES: NASTRAN Finite Element ProgramD o e . , U o , t / A q q - / - o 6 4 , l / L D
y ' r + t , t , ' 4 t ? 4 u t c g . A u r r . D ' | t , ( t u r e n , 4
CALCULATIONS: (SEE ATTACHED)
CONCLUSIONS: The minimum factor of safety against elastic buckiing for vacuum loadingis 5.9.
NOTES:
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NO:Vo41-t-o6t
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R,=*, oDoc. No, Vo49- l -069t r r 9 o e 9
1+ (toa4\ '
PROCESS SYSTEMS INTERNATIONAL. INC.WESTBOROUGII MA
ENGINEERINGCALCULATIONS
NO: V049-1-104PAGE l OF C
REV. DEO# DATE BY: CHECK TITLE: Beam Splitter Chamber -Nozzle D Anahsis for 2(n ke Forceo 6 L?3 1n tq( faa c- tltlDb
RY R D Ciatto DEPT ' ?44
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE: Evaluate nozzle D ofthe BSC for 200 kg load specified by the LIGO project.
mtHOO: Hand calculations for overall stress analysis of nozzle and FE analysis to determinedetailed stresses.
ASSIIMPTIONS: 1. Force is transverse to nozzle centerline.2. Force is applied uniformly about circumference at end ofnozzle.
IMUTS: LIGO project drawing V049-4-001 - Beam Splitter Chamber.Calc. No. V049-1-066, StruAural Design Criteria
REFERENCES: SeeINPUTS
CALCULATIONS: (SEE ATTACI{ED)
CONCLUSIONS: The resulting stresses from the imposed nozzle D forces are low andthe structural integrity ofthe nozzle and shell are not affected by this load,
NglEL-See load cases 4 and 5 of computer file BMSPLI12.* for the Images FE model results.
Revision No. 0Doc. No. V049-l-104Page I of 9
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PROCESS SYSTEMS INTERNANONAI, INC.WESTBOROUGH,MA
ENGINEERINGCALCULATIONS
No: y 'o ' / 2 - / - o? /PAGE 1 OF 2
REV. DEO # DATE BY: CHECK Vacuum Equipment Seismic Acceleration0 oJ 2-8 t2/n/7 lz /)c- , D b
BY: 9 . ( / / . r 1 - a DEPT-t 744
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. To determine marimum seismic acceleration factors for design of LIGO vacuwn equipment.
METHOD: Hand calculation using applicable construction code.
ASSUMPTIONS:
INPUTS: LIGO - E940002-02-4, Vacuum Equipment Specification, Rev. 2, September 6, 1995
REFERENCES: 1. LIGO Specification (above)2. ASCET-S8, American Society of Cival Engineers - Minimum Design Loads for Buildings and OtherStructures
i . > ) " - l r , y ' e . / 9 - / ' a 6 4 , l t t D y ' a c " t ; ' * t t { e i : t o a p l z 4 , t e r - ,DEs r t - l 1 ,a r . f t , , ,n- .
CALCULATIONS : (SEE ATTACFIED)
CONCLUSIONS: The maximum seismic acceleration factor is .05625G. This factor will be applied toequipment weight in static analyses.
NOTES: The maximum seismic zone for LIGO equipment is Zone 1.
o o o
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Doc- Fto. VOrR-t -o?t€ - r . z " I 7
PRO9ESS SYSTEMS INTERNATIONAI, INC,WESTBOROUGH,MA
ENGINEERINGCALCULATIONS
NO: V049-1-032PAGE I OF l.3
REV. DEO # DATE BY: CHECK TITLE: Comoonent Interface Loads0 /3. ' l4z.//9i /28-- A c.} t(
BY:11 . O . ( ' , t * z - i ' DEPT.:.744
PROJECT: LIGO Vacuum Equipment PROJECT NO: V59049
PURPOSE: Detennine vacuum forces on component flanges due to the venting of certain sections of tlesystem while other sections remain under vacuum.
METHOD: Hand calculation methods of statics are used to determine unbalanced vacuum loads on:r Beam Splitter Chambers. Horizontal Access Moduleso Gate Valveso 80K Pumps
ASSUMPTIONS: Beliows impose negligible axial forces on components. Adapters and valves have noaxial restraint.
INPUTS: PSI Equipment Arrangement Plans and spool piece dwgs. Atmospheric pressure -- 14.7 psi.
REFERENCES: Senior Flexonics, lnc. - Prelim. Design Calculations of LIGO Vacuum Equipment -
Bellows (attached).
CALCULATIONS: (See Attachment)
CONCLUSIONS: See surnmary on following sheet.
NOTES: This calculation may be used to detemine vacuum forces on adapters, spool pieces and tubes.
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:a-RESULTS
SPRING RFTESTHEORE ICAL SpRINE RATE = a,929. E7wORKING SFRING RATE = 7.69.4.44LATERAL SPRING RATE = g. iZZC*ASLCTERAL OI4ENT RATE = I.A15E+A6ANGULAR EOMENT RATE = grsgg-S8TORSION MOI|IENT RATE = 3.955E+O7
MOVE'IENTSCONVOLUTION GAF.COIIItrRESION DUE To Ax IAL iIovEHENTEXTENSION DUE TO AXIAL FTOVEI4ENTnxlnL DISp. DUE TO LATERCL OFFSET =NXIAL DIsF.. DUE To ANG, RoTATI0N =FnX. EOUI UFLENT Ax IAL COtittrR€SSIoN =NFX. EOUIVALENT AXIAL EXTENSTONHfix. EQUMLENT AXIAL r,tOvEhENT
STRESSES EJII4A5 l = ? 6 4 4 p s i91r = N. /AS? = 3AG4 psiS?t =N/ASar r =N/nS g = 4 8 O . 5 D s iS 4 ( . 3 5 ) = 7 e e ? p s rSg = 7A4.7 pEi66 - 1489OO peiST E IS6GAO osi
l b f / i nl b f / i nl b f / i ni n - l b s . / i ni n - I b s / d e 9i n - l b s / d e g
i n / c o n v .g . 9 5 4 1 Ao. 750aoo. oBo€roo. aaooo0. 80aEoet. 75AO@o. &c|a6e|B. 7546E|
EJFA FACTBRScp = .65s1trf = 1. 463Cd = 1. 74Cr = N/Flc t = 1 OEA - 19aSH t . - 1 7 , 3 4LCX= N./A
OTHER DCTACYCLE LIFESOUI RH FIRESSURE tr,OLD /E. ?3SQUIRTN PRES9URE HOT / E.AsEOU] U. PIPE T.'ALL THICKNESS
= 1 9 , 3 1 6= B3A= 7 9 5 . 5= .47g�6
c y c l e sp s i EP s i gl n
i n"aI b s .
Revision 0Doc-No. V049-1-032Page 2l of23
: i " / "
l l- l . lonlus lhc.
SENIOR FLEXONI CSCI RCULER BELLOI.IS
(UNFEINFORCED SIN6LE)
sYsTEtvts
-_-. Gjo_e
4 8 i n E . J .RIJN FY: LDC
HNTERIAL INFORMFT IONBELL$. Is ATERIAL SECT. VI ITsAe40-3A4C-fiod. of E. = e. B3E+O7H-i lod. of E.= Z.6B6SE+O7S a - 1 5 4 1 ? F s i
BDEIJFTOiIER: F,ROtrESSJOB *rDnTE : S/?z/95
INPUTED DATA1) Db = L D. OF BELLOWS?) n = NUITIBER oF F,LIES3) t = NOl't, THX. OF I pLy4 ) q = C O N V O L U T T O N F I T C H5) r.r - CONV HEI6HT (or OD)6) N = N8. OF CONVOLUTIONS7) F = F,RESSUREg) T = TEMFERATURE9) Lt = LENGTH TANGENT
10) tc = THTCKNEgS OF CBLLFR11) Lc = LENGTH COLLtrR
^ ol.-'u t
13) Ec = f fXIAL CBHFRESSI0N
BDCUSTOIIERr trROCESSJOB * !DATE : 5/?i/95
INF.UTED DATAr, Db = I. D. OF BELLUI,,5?) n = NUdAER OF FLIEE3) t = NOM. THK. gF I pLy4)q = t rOi l -vbLUTION FrTCH5) r,r = CONV HEI6HT (or OD)6) t{ = NO, OF CONVOLUTTONS7) F = PRESSURE6! T = TEi'TPERFTURE9) Lt = LENGTH TBNGENT
lB) tc = THICKNESS OF CALLAR1t) Lc - LENGTH COLLFR1e) Ee = AXIAL EXTENSION13) Ec = FXIAL CO|{trRESSION14) Y+ = +t ve Lf,TERnL OFFSET15) Y- = -' ve LATERAL AFFSET16) fiN = CNGULAR ROTnTTAN
0 5 / 2 6 / 9 5 l t : 0 6 g2r0 629 8ro0 FLEX.ON I CS UlC..:_
SENIOR FLEXONICSEI RCUL']R BELLOIIS
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SYSTEhS
A oog
60in E. J .RUN BYI LDC
IIFTERINL INFOR�TATIONEELLOI.IS fiETERIAL SECT. VI I I64e40-304C-frtsd. of E. = ?. B3E+OZH-l r lod. of E. = e.6B6gE+OzE a = 1 6 4 1 e p 3 i
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[vrvuuar*'
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Rcvision 0Doc. No. VM9-l-032Page22 of23
FESULTS
SPRING RATESTI. IEORET t CCL SPRING RATE = S,683_ A3 rbf . / inht t lRxrN6. StrRIN8 RATE = r ;943. 34. lb f / inLATERAL StrRING RAIE - - = r . rgrE+a6. lb f . / in
\ . rz t \ LRTERAL I IOMENT RATE = ?. €6lE+G6 in- lbs. / in" ; i ; . - > ! ! ! !LAR i4oHENT RErE = 16,446.e6 in- lbs/des"hf tc l l TORSION HOHENT f iATE = 7.?t7E+e7 in_ lbs/c ,e i
i n l c o n v .= G . 9 6 4 l O= 8.75900= o. OOAOo= 9. GAOGO= G. AOOOO= O. 7SQ|OO- A. OOOGO= O,79O@Q
STRESSES EJI'IFSl = €E45El t = N/A
EJITR FACTORSc p = . 5 7 0 1C f - 1 . 5 O 6C d = r . 6 9 ttrr c N/AC t E l gEA = 3Q43H t . = e I . 6 7LCt l= N/A
MOVE!,lENTScoNuo|-uTtoN 6cFCOfiPRESION DUE TO AXINL HOUEftENTEXTENSION DUE TO AXIAL IIOVEdENTAXIEL DISP. DUE TO LATERAL OFFSETAXIAL DISF. DUE TO ANG. ROTATIENiIAI. EOUI UALENT AXINL COMPRESSION
AX. EAUI UALENT AXINL EXTENSIONI{AX. EQUI UALENT AXIAL N'OVEMENTOTHER DATACYCLE LIFESOUI RI{ F'RESSURESOUIRM PRESSUREEOUI U. PIPE I.IALL
= 1 6 , 4 e A c y c l e s , ,COLD /?.e5 = rg.?? peigH O T / . e . U S = . 9 2 O _ J p s i g
THICKNESS = .8706 in
/I S*vrtz'T c^ .eev*L LJttt, o" (tee,
. { r t / ! i i / t o l J : v r E i z . t | , 0 J ! o r g u
BDCUSToMER: FR0CESS SYSTE'4SJOB t rDFTE : 5/e3/95
INF'UTED DATA1) Db = I. D. OF BELLOr.lse) n = NUIT|BER OF trLlES3) t = NOtq. THK. OF I FLy4 } q = C O N V O L U T I O N P I T e H5 ) r,r = CONV HE I6HT ( or OD)6l N G NB. OF CONVOLUTIONS7, F, = PREASURE8) T = TEfiFERATURE9) Lt = LENGTH TANBENT
10) tc = THICKNESS OF COLLAR11, Le = LENGTH COLLfiRle, Ee = nxIAL EXTENSION13) Ec = AXIAL GOf4FRESSION14) Y+ = +r ve LITERAL OFFEET15) Y- = - ! ve LFTERAL 8FFSET16) QN = ANEULRR RoTATISN
f IJAUI\ r !lJlll-. __
SENIOR FLEXONICSCIRCULAR aELLOtIS
(UNREINFORCED SINGLE)
lgoo{
= 7 E= 1= . 0359= ?- ? . e 3= ?= 1 3= 347= l . E= o= A l= o
= o= t t= a
1 D
i ni ni n
PE i.gd e g Fi ni ni ni ni ni ni nd e q
T e i h E . J .RUN BY: LDC
NTERIAL INFOR]TIf,TIONBELLOI.'S IICTERI EL SECT. V I I Isne4Q-3G4C-ltloct. of E. - e. g3E+EzH-t lod. of E.= a.6A65E+O7S a = 1 6 4 1 e p s i
RESULTS
SPRING RATESTHEORETICAL SPRI i IG RATE = 4.?rO.@A lbf l inI IORKINF SFRINE RATE = e,?A9.71 lb f / i r rLATERAL SFRING RATE = r . S93E+O6 rbf / i r ,LATERAL '{OHENT RATE = 3. ?SZE+O6 io_lba/innNEULCR fTIOHENT RBTE = e7t5,Aj.77 in_tbs/deETBRSION l lqr fENT RFTE = r .3BBE+OA in- lbs/deB
i n / e o n v .= O . 9 6 4 1 9 |= O.75OcO= O. SGQOO= 9. &OOAO= O. OOQAA= O.75AaO= O. AOOOA= O.75aBa
g.TREASES EJEFSr = 936s ps iS l i = N / ASg = 55Ar p5iS?r =N/trS€t t =lrl.ze53 = 477. t ps iS a ( . 3 E ) = 7 e t 5 p s iSS = 759. t ps i56 = 1479OG pr iST = 1E34OO psi
MOUEMENTSCONVOLUTION BAPCO!'PRES t ON DUE. TO AXIAL ITIOVEMENTEXTENSI ON DUE IO AXIFL iIOUEMENTAXIEL DISP. DUd TO LATERAL OFFSETAXIH- DIBF.. DUE TO ANG. BOTATTONIIAX. EOUI VNLENT NXIAL COFTtrRESSION
AX. EEUI VALENT AXINL EXTENSIT}N!|nX, EQUI VALENT AXIAL dOVEIIENTOTHER Df,TNCYCLE LIFESEUIR PRESSURESAUI RII FRESSUREEOUI V. PIFE T.JALL
EJ]NA F€CTORSc p - . 6 7 9 eCf = l . 535C d = 1 . 6 7Cr = N/€C t = 1 6En = !1334lJt . = A6LCtrl= N.rn
= 15, eso cyel E Eco�LD /?. ?5 = tZO6 ps igH O T / e . e 9 - 1 1 4 5 P s i q
THICP.NESS = .87O6 in
in"?I b s .
Revilion 0Doc. No. VM9-1-032PaEe23 of23
a
o
PROCESS SYSTEMS INTERNATIONAL, INC.WESTBOROUGEMA
ENGINEERINGCAICULATIONS
NO: V049-l-042PAGE 1 OF 37
REV. DEO # DATE BY: CHECK Bolted Flenge Analysis For Tensile Forces0 // 2J'/76 12 > C-/ AC.A.
BY: DEPT.:744
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. Analyze and evaluate flanges and bolts for large tensile forces resulting from normaloperation from venting ofparts of systems when gate valves are closed.
METHOD: Hand calculations for forces using statics analysts.Finite element analysis of bolted flange using IMAGES program.
ASSUMPTIONS:
INPUTS: 1. Positive purge pressure = 2 psig.2. Atrnospheric pressure = 14.7 psig.3. Component interface loads.
REFERENCES: 1. IMAGES - 3D, Version 3.0, R.L. Cloud and Associates.2. Calc V049-l-032. Component lnterface Loads
CALCULATIONS : (SEE ATTACFDD)Appendix A: Confirmalory Hand CalculationsAppendix B: Analysis of Bolt PryiagAFpendix C: Test Pressure to Observe Flange Behavior Under Tension
CONCLUSIONS: The 30 1/4 in. flange has the maximum bolt force. The number of bolts is increasedto 24 for this flange and the bolt preioad is increased to 10,000 lb for all flanges.
NOTES: Computer file: FLANGEC.*I
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PROCESS SYSTEMS INTERNATIONAI,, INE,WESTBOROUGEMA
ENGINEERINGCALCULATIONS
NO: V049-l-PAGE I OF8
REV. DEO# DATE BY CHECK TITLE:.|4n Gfie Valvr
IVeld Stub/Beam TubeBuckling itress Evaluation
0 3 q ? tlt6t% Po<- \^JE6
BY: R. D. Ciatto DEPT.: 744
PROJECT: LIGO Vacuum Equipm€,nt PROJECTNO: V59M9
PURPOSE: This is an infoirrution calculation that evalu:ites the fus of a partial penetration weldon the buckling resistance of the GNB gate valve weld stub. It also evaluates tltepotetrtial buckling ofthe end ofthe CBI tube at tle anchor in the beam tub€.
METIIOD: Iland calculations are performed using the compressive stress formulas of the ASI\tlE Code.
ASS{IMPTIONS: For the calculation oftlre bending stress due to valve weight, the "soft" zupportrmder the valve is neglested. This is conservative since the reaction provided bythis support relieves the cafltilever effect ofthe valve.
IMUTS: 1. Vacuum Press.re = -14.7 psi2. Maximum Temperature = 400oF3. Valve Weight = 8000 lb
REFERENCES: l. ASME Boiler & Pressure Vessel Codg Section VIil, Div. i2. GNB Calculatioq 'qf,)uct Neck Welds", Oct. 25,1996.3. AISI Suinless Steel Cold-Formed Structural Desim Manual
CALCULATIONS: (sFF. ATTACI{ED)
CONCLUSIONS: Bending stresses due to the weight of the valve are compressive at the bottom theweld shrb and beam tube. Although these stresses are low (< 700 psi), they add to the axial compressivestresses due to e:�rternal pressure. The combined stresses are less than tlle compressive stress allowedby the ASME Code.
NOTES: The weld stub has adequate buckling resistance even witl the partial penetration longitudinalweld in tle stub.
PROCESS SYSTEMS INITRNAfiONAI. INC,WESTBOROUGH.MA
ENGINEERINGCALCULATIONS
NO: VlX9-l-122Rev. No. 0Pme 2 of E
PROJECT: LIGO VACtt{tM EOIIIPMENT PROJECTNO: v59{X9CALCT LATION TITLE: 44'Gate Valve Weld Stub/Beam Tube BucHiig SEesr Ey{gei{gn-
)
I
o
TABLE OI'CONTENTS
Revision History
Weld Strb - As Designed Condition
Weld Stub - Reduced Thickness
Stress at CBI Anchor
Alternate Code Evaluation
4
f
6
o
a
REVISION IIISTORY
Rev.0 Original Issue - Nov. 1996
PROCDSS SYSTtr.MS INIE.RNATIONAL. INC.WESTBOROUGH,MA
ENGINEERINGCALCULIL'TIONS
NO: V0491-122Rev.No.0Pase 3 of E
PROJECT: LIGO VACULIM EOIJIPMENT PROJECTNO: v59049CALCTILATION TITLE: 44'Gate Valve lYeld StublBeem Tube Bucklins Str6s Evaluatiotr
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PAGE NO. 1ID: Process Systens Internatj.o
* * * * * * * * * * * * * * * * * * * * * ! : i : i * * * * * * * * * * * * * * * * * * * * * * * * * * *
* ** S T A A D - I I I ** Rev i s ion 21 .0 ** Proprietary Proqran of ** Research Engineers, Inc. ** Date= l[AR 23, L995 ** T i n e = 1 2 : 3 2 : 3 3 ** *lt USER ID: Process Systens International ** * * * * * * * * * * * * * * * * i * * * * * * * * * * * * * * * * * * * * * * * * i f * * * * * * * *
1. STAAD SPACE PIPE BRIDGE2. INPIN WIDTH 723 . TTFILE NAI'IE:ARTROU4. *PTPE BRTDGE5. I'NIT INCHES POUND5. JOINT COORDINATES7 . L O O . O . 0 . r 2 0 0 . 1 0 8 . o . r 3 0 1 0 2 . 1 o 8 . O . r 4 0 2 0 4 . 1 0 8 . o .8 . 5 0 2 0 4 . 0 . 0 . t 6 0 o . O . - 7 2 . i 7 0 0 . 1 o 8 . - 7 2 . , a o I o 2 . L o a . - 7 2 .9 . 9 0 2 O 4 . l 0 a . - 7 2 . ; 1 0 0 2 0 4 . O . - 7 2 .
10. UEXITBER INCIDENCES1-L . Loo L0 20 ; 101 20 30 r 102 30 40 ; 103 40 50 r 200 60 ?o , 20 I 70 aoL2 . 202 80 90 ; 203 90 1001 300 20 70 t 30 r . 30 70 t 302 30 80 r 303 30 901 3 . 3 0 4 4 0 9 014. },TEUBER PROPERTY AUER15. 100 TO LO3 200 TO 203 300 302 304 TABLE ST TUBE TH 0.25 WT 4. DT 6.16. 3O]. 3O3 TABLE ST TUBE TH 0.25 WT 4. DT 3.1.7. SUPPORTS18. 10 50 60 L00 FIXED BUT uX !{y MZ19. CONSTANTS20. E 27999998. AIL21. DENSITY 0.283 A],L22. POISSON 0.3 ALL23. BETA O. ALL24. E STEEL ALL25. POISSON STEEL ALL26. IOAD 1 TRUSS SETFWEIGHT (Dt )27. SELFWEIGHT Y -1.28. LoAD 2 PrPE LOADS (D2)29. JOINT LOAD3 0 . 2 0 F X 3 1 . F Y - 5 5 0 . F Z 3 L .3L . 30 FX 31 , . FY -s50 . EZ 3 I .3 2 . 4 0 F X 3 L . F Y - s 5 0 . E Z 3 7 .33. I,IEMBER LOAI)3 4 . 1 0 0 C O N G X I 2 . 7 5 4 . O .3 5 . 1 0 0 C O N G Z r 2 . ! 5 4 . O .3 6 . 2 0 0 C O N G X 1 2 . L 5 4 . 0 .3 7 . 2 0 0 C O N G Z 1 2 . 1 5 4 . 0 .3 8 . 1 0 3 C O N G X 1 2 . L 5 4 . 0 .3 9 . 1 0 3 C O N G Z 1 2 . 1 5 4 . 0 .4 0 . 2 0 3 C O N G X 1 2 , 1 5 4 . 0 .4 I . 2 0 3 C O N G Z 1 2 . 1 5 4 . 0 .
-Re,, o-.Qoc. J-{o, Vo41 - t -6n / -2 . 7 o F l ?
PIPE BRIDGEID: Process
-. PAGE NO. 2Systems hternatio
4 2 . 3 0 04 3 . 3 0 044 . 30245 . 3024 6 . 3 0 44? . 3044 8 . 1 0 14 9 . 1 0 150 . 1025 1 . 1 0 252. 20Ls 3 . 2 0 154. 20255. 2025 5 . 3 0 157 . 30 r5 8 . 3 0 35 9 . 3 0 36 0 . 3 0 05L . 3006 2 . 3 0 06 3 . 3 0 06 4 . 3 0 05 5 . 3 0 05 5 . 3 0 067 . 3006 8 . 3 0 06 9 . 3 0 07 0 . 3 0 07 L . 3 0 072 . 3007 3 . 3 0 074 . 3007 5 . 3 0 07 6 . 3 0 077 . 3007 8 . 3 0 07 9 . 3 0 08 0 . 3 0 08 1 . 3 0 08 2 . 3 0 08 3 . 3 0 08 4 . 3 0 08 5 . 3 0 08 6 . 3 0 08 7 . 3 0 08 8 . 3 0 08 9 . 3 0 09 0 . 3 0 29 L . 3 0 29 2 . 3 0 293 . 3029 4 . 3 0 295 . 30296. 30297 . 302
CON GXCON GZCON GXCON GZCON GXCON GZCON GXCON GZCON GXCON GZCON GXCON GZCON GXCON GZCON GXCON GZCON GXCON GZCON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GYcol'I GzCON GXCON GY
CON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GYCON GZCON GXCON GY
8 . 0 7 3 6 . O .8 . 0 7 3 5 . 0 .8 . 0 7 3 5 . 0 .8 . 0 7 3 5 . 0 ,8 . O 7 3 6 . 0 .8 . 0 7 3 6 . 0 .1 1 . 1 5 1 . 0 .1 1 . 1 5 1 . O .1 1 . L 5 L . o .1 1 . 1 5 1 . 0 .1 L . 1 5 1 . O .1 1 . 1 5 1 . 0 .1 r . . 1 5 1 . O .1 L . 1 5 1 . 0 .6 . 6 6 2 . 4 3 0 .6 . 6 5 2 . 4 3 0 .6 . 6 6 2 . 4 3 0 .6 . 6 6 2 . 4 3 0 .6 2 . 1 0 . O .- 1 1 0 0 . 1 0 . o .6 2 . 1 0 . O .3 1 . 2 0 . 0 .- 5 5 0 . 2 0 . O .3 1 . 2 0 . O .2 . 2 5 2 5 . 2 5 0 .- 4 0 . 2 5 . 2 5 0 .2 . 2 5 2 5 . 2 5 0 .2 . 2 5 2 9 . 7 5 0 .- 4 0 . 2 9 . 7 5 A .2 . 2 5 2 9 . 7 5 0 .2 . 2 5 3 4 . 2 5 0 .- 4 0 . 3 4 . 2 5 0 .2 . 2 5 3 4 . 2 5 0 .5 . 0 6 3 4 0 . 0 .- 9 0 . 4 0 . o .5 . 0 6 3 4 0 . 0 .5 . 0 6 3 4 7 . 5 0 .- 9 0 . 4 7 . 5 0 .5 . 0 6 3 4 7 . 5 0 .8 . 4 4 5 5 . O .- L 5 0 . 5 5 . O .8 . 4 4 5 5 . O .5 . 0 6 3 6 2 . s O .- 9 0 . 6 2 . 5 0 .5 . 0 6 3 6 2 . 5 0 .8 . 4 4 7 0 . 0 .- 1 5 0 . 7 0 . 0 .4 . 4 4 7 0 . O .6 2 . 1 0 . 0 .- 1 1 0 0 . 1 0 , 0 .6 2 . 1 0 . 0 .3 1 . 2 0 . 0 .- 5 5 0 . 2 0 . 0 .3 1 . 2 0 . 0 .2 . 2 5 2 5 . 2 5 0 .- 4 0 . 2 5 . 2 5 0 .
tFFo.=.""o. vbql-roltE l o o F t 1
t
PIPE BRIDGE
9 8 . 3 0 2 C O N G Z 2 . 2 5 2 5 . 2 5 0 .99 . 302 CON GX 2 .25 29 .75 0 .
100 . 302 coN GY -40 . 29 .75 0 .1 0 1 . 3 0 2 C O N G Z 2 . 2 5 2 9 . 7 5 0 ..o2 . 302 CON GX 2 .25 34 .25 0 .
1 0 3 . 3 0 2 C O N G Y - 4 0 . 3 4 . 2 5 0 .1 0 4 . 3 0 2 C O N G Z 2 . 2 5 3 4 . 2 5 0 .1 0 5 . 3 0 2 C O N G X 5 . 0 6 3 4 0 . 0 .1 0 5 . 3 0 2 C O N G Y - 9 0 . 4 0 . 0 .7 0 7 . 3 0 2 C O N G Z 5 . 0 6 3 4 0 . 0 .1 0 8 . 3 0 2 C O N G X 5 . 0 6 3 4 7 . 5 0 .3 .O9 . 302 CON GY -90 . 47 .5 0 .1 1 0 , 3 0 2 C O N G Z 5 . 0 6 3 4 7 . 5 0 .1 1 1 . 3 0 2 C O N G X 8 . 4 4 5 5 . 0 .112 . 302 CON GY -150 . 55 . 0 .!L3 . 302 CON GZ 8 .44 5s . O .L r . 4 . 3 0 2 C O N G X 5 . 0 5 3 6 2 . 5 0 .1 1 5 . 3 0 2 C O N G Y - 9 0 . 6 2 . 5 0 .1 1 6 . 3 0 2 C O N G Z 5 . 0 6 3 6 2 . 5 0 .! I 7 . 3 0 2 C O N G X 8 . 4 4 7 0 . 0 .1 1 8 . 3 0 2 C O N G Y - 1 5 0 . 7 0 . 0 .1 1 9 . 3 0 2 C O N G Z 8 . 4 4 7 0 . O .720 . 304 CON GX 62 . 1 ,0 . 0 .t 2 I . 3 0 4 C O N G Y - 1 1 0 0 . L 0 , 0 .I22 . 304 CON GZ 62 . rO . O .723 . 304 CON GX 31 . 20 . 0 .t24 . 304 CON GY -550 . 20 . 0 .) -25 . 304 CON GZ 31 . 20 . 0 ,L 2 6 . 3 0 4 C O N G X 2 . 2 5 2 5 . 2 5 0 .I27 . 304 CON GY -40 . 25 .25 0 .1 2 8 . 3 0 4 C O N G Z 2 . 2 5 2 5 . 2 5 0 .. 2 9 . 3 0 4 C O N G X 2 . 2 5 2 9 . 7 5 0 .
1 ,30 . 304 coN GY -40 . 29 .75 0 .1 3 1 . 3 0 4 C O N c Z 2 . 2 5 2 9 . 7 5 0 .1 3 2 . 3 0 4 C O N G X 2 . 2 5 3 4 . 2 5 0 .1 3 3 . 3 0 4 C O N G y - 4 0 . 3 4 . 2 5 0 .1 3 4 . 3 0 4 C O N G Z 2 . 2 5 3 4 . 2 5 0 .r . 3 5 , 3 0 4 C O N G X 5 . 0 6 3 4 0 . O .1 3 6 . 3 0 4 C O N G Y - 9 0 . 4 0 . 0 .I 3 7 . 3 0 4 C O N G Z 5 . 0 6 3 4 0 . O .1 3 8 . 3 0 4 C O N G X 5 . 0 6 3 4 7 . 5 0 .1 3 9 . 3 0 4 C O N G Y - 9 0 . 4 7 . 5 0 .1 4 0 . 3 0 4 C O N G Z 5 . 0 6 3 4 7 . 5 0 .L 4 1 . 3 0 4 C O N G X 8 . 4 4 5 5 . 0 .r42 . 304 CON GY -L50 . 55 . 0 .1 4 3 . 3 0 4 C O N G Z 8 . 4 4 5 5 . 0 .1 4 4 . 3 0 4 C O N G X 5 . 0 6 3 6 2 . 5 0 .745 . 304 CON Gy -90 . 62 .5 0 .1 4 5 . 3 0 4 C O N G Z 5 . 0 6 3 6 2 . 5 0 .r 4 7 . 3 0 4 C O N G X 8 . 4 4 7 0 . O .L 4 8 . 3 0 4 C O N G Y - 1 5 0 . 7 0 . 0 .r . 4 9 . 3 0 4 C O N G Z A . 4 4 ? O . O .150. LOAD COIIB 31 5 1 . 1 1 . 2 L .152. PERF'OR!,T ANALYSIS
-- PAGE NO. 3ID: ProceFs systeng Internatio
R r=-v oDoc , r vo , Voq1 ' t ' o1 lP . i l aF - i ?
PIPE BRIDGE
P R O B L E ! { S T A T I S T I C S
NIJI.IBER OF JOINTS/MEMBER+ELH{ENTS/SUPPORTS = Lo/ L3/ 4oRIGINAL/FINAL BAND-WIDTH = 6/ 3TOTAL PRII,IARY LOAD CASES _ 2, TOTAL DEGREES OF EREEDOM = 48SIZE OF STIFFNESS MATRIX = 1152 DOUBLE PREC. IvoRDSREQRD/AVAIL. DISK SPACE = L2.o3/ 378.2 VB. EXIIEI'! = 6.69 !'lB
-- PAGE NO. 4ID: Proce-ss systems Internatio
++ PROCESSTNG ELEI,IENT STIFFNESS UATRIX.++ PROCESSING GLOBAL STIFFNESS UATRIX.++ PROCESS]NG TRIANGUI,AR FACTORIZATION.++ CALCULATING JOINT DISPLACEUENTS.++ CALCUI.ATING I,IEI,IBER FORCES.
153. *PRINT I1IATSRIAL PROPERTIES ALL1.54. *PRINT JOINT COORDINATES ATL155. TTPRINT SUPPORT INFORMATION ALL156. IIPRINT !4E!,IBER INFOR}IATION ALL157. *PRINT UruBER PROPERTIES ALL158. PRINT JOINT DISPLACEMENTS AI,L
L 2 . 3 2 2 3 5L2.32r3772.32 r37L2 2 32.37L2.32r38
S#f,., vo41-t-o'1ta r4 o.F_..t?
BRIDGE
JOINT DISPLACE!.IENT (INCH RADIANS)
LINT
-. PAGE NO. 5ID: Process Systens Internatio
sTRUcfllRX TYPE = SPACE
8 0
l e 0L O 0
IOAD
123L231
312312312,l
I
2312'l
I2312
Z-TRANS
0 . 0 0 0 0 00 . 0 0 0 0 00 . 0 0 0 0 00 . 0 0 1 4 1o.27 ] -L4o . 2 7 2 5 50 . 0 0 1 4 6o . 2 4 5 1 8o .24655o. oo14Lo . 2 L 7 6 00 . 2 1 9 0 1o . 0 0 0 0 00 . 0 0 0 0 0o . 0 0 0 0 00 . 0 0 0 0 00 . 0 0 0 0 00 . 0 0 0 0 00 . 0 0 1 4 1o . 2 7 L r 9o .27 2600 . 0 0 1 4 6o.24522o . 2 4 6 6 8o.001,4Lo . 2 L 7 6 20 . 2 1 9 0 30 . 0 0 0 0 0o . oooooo . 0 0 0 0 0
10
2 0
3 0
4 0
50
6 0
7 0
X-TRANS
0 . ooooo0 . oooo00 . 0 0 0 0 00 . 0 0 0 0 40 . 2 0 5 0 10 .20604o . 0 0 0 0 0o .20579o.2s579
- 0 . 0 0 0 0 4o .205540 . 2 0 5 5 0o . 0 0 0 0 0o . 0 0 0 0 0o. oooooo. oooo00 . 0 0 0 0 00 . 0 0 0 0 0o . ooo04o . 1 8 7 0 3o.747070 . 0 0 0 0 00 . 1 8 6 7 90 . 1 8 5 ? 9
- o . 0 0 0 0 40 . 1 8 5 5 1o . L a 6 4 70 . 0 0 0 0 0o . 0 0 0 0 0o . o 0 0 0 0
Y-TRANS
o. ooooo0 . 0 0 0 0 00. ooo00
-o . oo027-o . 00286- 0 . 0 0 3 1 - 3- o . 0 3 5 3 9-o .24067-o .27606- 0 . 0 0 0 2 7- o . 0 0 3 0 5- o . o o 3 3 3
o . o o 0 0 00. oooooo. ooooo0. ooooo0. oooo0o . 0 0 0 0 0
- 0 . 0 0 0 2 7- 0 . 0 0 0 4 7- 0 . 0 0 0 7 4- 0 . 0 3 0 3 0- o . 1 2 8 5 0- o . 1 5 8 9 0- 0 . 0 0 0 2 7- 0 . 0 0 0 7 9- o . o 0 1 0 5
o . 0 0 0 0 0o . o 0 0 0 00 . 0 0 0 0 0
X-ROTAN
0 . 0 0 0 0 30 . o 0 3 8 40 . o o 3 8 7
- 0 . 0 0 0 0 3- 0 . 0 0 0 1 5- 0 . 0 0 0 1 8
o . 0 0 0 0 20 . 0 0 0 8 4o . 0 0 0 8 5
- 0 . 0 0 0 0 3-0 . oo023- 0 . 0 0 0 2 6
0 . 0 0 0 0 30 . o 0 3 L 4o . o o 3 1 7
- 0 . 0 0 0 0 10 . 0 0 3 3 0o . 0 0 3 3 00 . o o o 0 5o . 0 0 0 9 4o . o o 0 9 9o . 0 0 0 1 0o . 0 0 1 9 90 . 0 0 2 0 9o . o 0 0 0 50 . 0 0 0 9 0o . 0 0 0 9 5
- 0 . 0 0 0 0 10 . 0 0 2 5 80 . 0 0 2 5 7
Y-ROTAN
o. oooooo . 0 0 0 2 2o . 0 0 0 2 20 . 0 0 0 0 00 . 0 0 0 2 2o .ooo22o . oooo0o . ooo25o. ooo250 . 0 0 0 0 0o . ooo23o . ooo230. oooooo . 0 0 0 2 3o , ooo23o . 0 0 0 0 0o . 0 0 0 2 8o . 0 0 0 2 8o . 0 0 0 0 00 . 0 0 0 2 8o . o o 0 2 80 . 0 0 0 0 0o . o o o 2 70 .00027o . oo000o . ooo30o .000300 . oooooo . ooo300 . 0 0 0 3 0
Z-ROTAN
o . 0 0 0 1 6- 0 . 0 0 1 4 5- 0 . 0 0 1 2 9- 0 . 0 0 0 3 3- 0 . 0 0 2 8 6-0 . 00318
0 . o0000o . 0 0 0 4 2o . ooo420 . 0 0 0 3 30.00r .05o . o 0 1 3 8
- 0 . o o 0 1 6- 0 . 0 0 3 3 7- 0 . 0 0 3 5 3
0. ooo15- 0 . 0 0 1 s 9-0 . 00144- 0 . 0 0 0 3 1- 0 . 0 0 2 0 3- 0 . 0 0 2 3 4
0 . 0 0 0 0 0o . o 0 0 3 90 . o o o 3 90 . 0 0 0 3 1o. ooo440 . 0 0 0 7 5
- 0 . o o 0 L 5- 0 . 0 0 2 8 0- 0 . 0 0 2 9 5
************** END OF LATEST ANAIYSIS RESULT **************
159. *PRINT I{E!,IBER FORCES AI,L160 . *PRINT I,IEMBER STRSSSES ALL161. PRINT SUPPORT REACTIONS
PIPE BRIDGE
SUPPORT REACTION5 -UNIT POI'N INCH
-- PAGE t{O. 6ID: Proce_ss Systens Internatio
STRUCIIRE TYPE = SPACE
Jr"r r.oADI23123123123
1 0
5 0
FORCE-X
50 .701 4 4 . 5 01 9 5 . 2 0-50 .70
- 4 6 4 . 4 7- 5 1 5 . 5 5
4 9 . 0 34 2 . 5 r9 1 . 5 4
- 4 9 . 0 3- 3 4 0 . 8 L- 3 8 9 . 8 4
FORCE-Y
3 9 0 . 4 53 4 5 4 . 0 13444 .45
3 9 0 . 4 53694 .524 0 8 8 . 9 7
3 9 0 . 4 5566 .27956 .7 23 9 0 . 4 59 5 1 . 2 0
1 3 4 1 . 6 4
FORCE-U
- 3 . 3 0-215 . 09- 2 1 8 . 3 9
- 3 . 3 0- 1 8 2 . 3 5- 1 8 5 . 6 5
3 . 3 0- 1 2 8 . 6 8- 1 2 5 . 3 8
3 . 3 0- 9 2 . 5 5-a9 .25
!.to!.{-x
0 . 0 00 . o 00 . 0 00 . 0 00 . 0 0o . o 0o . o 0o . o 0o . 0 0o . o 0o . o 00 . 0 0
t{ott-y
o . o o0 . 0 00 . 0 00 . o 0o . o oo . o o0 . o oo . o 00 . o 0o . o o0 . o o0 . 0 0
uou zo . o 0o . o0o , o 0o . o 0o . o 0o . o 00 . 0 0o . o0o . o oo . 0 00 . 0 0o . o o
50
100
************** El{D OF LATEST AI{ALYSIS RESULT * * * * * * * * * * * * * *
162. PARAMETER163. CODE AISCL64. }f.AIN 0. Atl1.65. WELD ].. ALL166. CHECK CODE ALT
IRr=rr O-Doc:No,
Vo41-,-oil-D.t4 os t9
P]PE BRIDGE
STAAD-III CODE CHECKING - (AISC)* * * * * * * * * * * * * * * * * * * * * * *
INCH (I,'NLESS OTHERWISE NOTED)
RESULT/ CRTTTCAL COND,/ R,ATrO,/FX MY YIZ
-- PAGE NO. 7ID: Process systens Internatio
LOADING/LOCATION
IAI.L UNITS
MEI{BER
ARE - POI,JN
TABLE
1OO ST TUB E
1O1 ST TUB E
102 ST tUB E
103 ST TUB E
2OO ST TUB E
2O1. ST TUB E
2O2 ST TUB E
203 ST TUB E
3OO ST TUB E
301 ST TUB E
302 ST TUB E
303 ST TUB E
304 ST TUB E
167. SELECT WELD
PASS3706 .97 C
PASS3 3 5 . 5 8 C
PASS362 .A7 C
PASS3 9 5 1 . 4 8 C
PASS81-9 . 23 C
PASS3 6 1 . 0 6 C
PASS4 0 7 . 2 2 C
PASSL 2 0 4 . L 6 C
PASSL 7 7 . A 7 C
PASS224 .27 T
PASS9 . 0 1 C
PASSL 0 3 . 1 8 T
PASS1 2 5 . 5 5 C
ALL
AISC- H1-322932.24Arsc- rr1-3
- 4 6 4 . 1 3Arsc- E1-3
- 3 9 8 . 9 9Arsc- H1-3
- 1 9 3 9 6 . 5 3Arsc- H1-3L 2 A 4 7 . 6 5Arsc- H1-3
2 2 7 . O 5AISC- fl1-3
3 3 7 . 9 3AISC- H].-3- 8 9 8 5 . 9 8AISC- H1-3
359 .43Arsc- H2-1
- 2 3 . L rArsc- Hl_-3
- 5 6 4 . 9 8AISC- H2-1
-28 .97AISC- H1-3
7 7 L . 0 2
0 . 3 9 3- 2 t 7 3 4 . 7 9
o . 4 4 465820 -25
o . 4 4 9-56632.07
o . 5 8 555027 .6L
o .792- 1 0 5 3 9 . 3 3
o . 2 4 t3 5 3 5 6 . 9 3
o . 2 4 L- 3 5 2 3 3 . 3 9
0 . 3 5 84L448 .94
0 . t_75257L3.20
0 . I 1 0- 5 8 9 6 . 9 0
0 . 0 4 5-5998 .97
o . 1 3 3-7 279 .46
0 . 1 5 62240L.43
31 0 8 . O 0
31 0 2 . O 0
3o . o 0
3o . o 0
3:_o8 . o0
31-02 . O0
3o . o 0
5
o . o 03
0 . 0 02
0 . o o3
7 2 . O O3
L 2 4 . 4 53
0 . o o
tRsrr or ioL. No.Vo49- l -dr I
. r f o F l q
PIPE BRIDGE
ALL TJNITS ARE - INCH
!.{E!.IBER LOCATTON/TOADING
ID: Proc€ss.. PAGE NO. A
gystems Internatio
STAAD-III IVELD DESIGN** * * * * * * * * * * * * * * * * * * *
POUN
WELD TYPE/HOR STRESS
WELD SrZElVERT STRESS
co!.tB sTREss/DIR STRESS
100
1 0 0
101
101
LO2
LO2
103
L o 3
2 0 0
2 0 0
20t
201
202
202
203
203
STA3
END,l
STA3
END3
STA,l
END3
STA3
ENDJ
STA1
ENDJ
5TAa
END3
STA
END3
STA3
END3
L 7 4 . 7 L
18 2 . 5 1
1
802 .92
12 7 0 . 6 0
I290 . 05
J.
4 3 9 . 5 L
1
4 6 . 2 8
1144 .52
11 0 0 . 3 0
L9 0 . 6 2
18 5 8 . 4 8
L4 2 4 - 8 0
14 4 4 . 3 5
L4 3 9 . 9 1
13 0 . 8 6
7 L . 4 0
L/161 s 6 . 1 6
2/L682 .92
L/L61 -29? .5a
3 /16397 .90
3/L54 9 9 . 3 1 .
2/168 0 0 . 9 1
3 /L6L34 .26
L/L64L2 .45
L/L67 3 . 2 3
tr lL642 .9L
t/L69 3 2 . 8 9
2/764 1 4 . 5 0
2 /16s 3 5 . 5 0
2 /L65 4 7 . 4 4
2/L6L 5 t . 0 9
r / t63Ir . A7
3 0 8 4 . 4 93075 .57
12567.55L2567.OO
LL632.567L532.O4
9 9 3 6 . 6 89925.02
LOO57.321 0 0 4 0 . 7 3
13151 . 09r3r!9.32
r2733.40t2732.6L
33gO .423 2 ? L . 7 4
7 7 5 . 3 a7 6 5 . 3 7
]-2369.7712369 .16
3032 .482 7 5 4 . 7 5
8 0 8 5 . 2 68 0 6 3 . 4 4
8 1 1 4 . 5 98 0 8 4 . 7 0
7 6 3 5 . 1 47 5 9 9 . 7 A
! 2 L 4 4 . 2 4L2143.25
1 1 1 9 . 9 91 0 7 3 . 3 2
R,:.voQoc, No.ql z. oF
vo{t- r -O4lI 1
PIPE BRIDGE
AI,L T'NITS ARE - INCH
!{E!.|BER LOCATTON/LOADING
STAAD-III WELD DESIGN** * * * * * * * * * * * * * * * * * * *
POUN
WELD TYPE/HOR STRESS
-. PAGE NO. 9Proce€s systens Internatio
couB sTREss,/DIR SIR'ESS
I D :
WEI,D SIZE/VERT STRESS
300
300
3 0 1
3 0 1
3 0 2
302
3 0 3
3 0 3
3 0 4
3 0 4
STA
END3
STA2
END?
STA
END3
STA2
END1
STAJ
END3
19 8 6 . 8 3
t9 6 0 . 8 6
L4ro.22
14 5 8 . 6 8
1
1 1 0 . 5 8
1'12 . 49
1
1 7 . 5 0
1
3 9 . 6 6
1767 .71 .
17 2 L . 4 0
TABULATED
L/162373.46
t/t67 9 5 . 3 L
t/L5620 .97
L/L67 5 e . t 7
r/L61 L 9 4 . t 8
L/L67 7 L . 9 2
t,/L61 2 0 . 3 1
7/L62 2 6 . 6 0
1/L62 1 5 5 . 1 8
t/L67 0 7 . 4 4
1 2 0 4 4 . 0 11L7 66 . 44
aa90 .628802 . 69
66L4.246572.24
4511 .284423 .39
1 4 0 5 . 3 57 3 2 . 6 L
3 0 8 0 . 7 529AL.59
6 3 5 9 . 3 96 3 5 8 . 2 3
7 9 L 2 . 7 57909 .4L
L O 7 2 4 . 0 2L O 4 7 7 . L 9
7 439 .257370 .27
* * * * * * * * * * * * * * * * * * END OF
1.68. STEEL TAKE OFF
WELD DESIGN *************** l r**
I
fft;||ltr,*t_,-*r
PIPE BRIDGEID: Process
STEEL TAKE-OFF
LENGTH( INCH)
1056 . O0249 .70
TOTAL t56L .79
* * * * * * * * * * * * END OF DATA FROI{ INTERNAI STORAGE ************
169. LOAD LIST170. IOAD LIST].71 . FINISH
*************** END OF STAAD-II I ***************
**** DATE: l,tAR 23 , 1"996 TIME= 12 : 32: 39 **rr*
* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * ** For questions on STAAD-III, contact: ** Research Engineers, Inc at ** Ph: (?I4) 974-25OO Fax: (7L4) 92L-2543 ** * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * i t * * * ! t * * * * * * * * * * * * *
-- PAGE NO. 10Systens Internatio
PROFILE
ST TUB EST TUB E
TIEIGHT(POUN)
L344.2932 I 7 , 4 9 3
AIT2 3
IRev o ----Doc NO. VO41- l - 01 |? , a o F ( t
ftr sIrj
\_:
iltr;i vr
rl I
:S
l s
st tS
!:d 3
'tR
:t * riiis
$Arr)
aLlrLJ\(r'\lc0IJ)gmdlnj$l
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fi
!:
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cl
PROCESS SYSTEMS INTERNATIONAL, INC.WESTBOROUGRMA
ENGINEERINGCA�-cULATIONS
NO: V049-l-107PAGE l OF 3l
REV. DEO# DATE BY: CIIECK TITLE: Welds for 60.5 in Nozzle to Shell Jointso D z i 3 R/t,/06 KO C-. LI ,Db
XlY. P T't Oirffn DEPT . ?A4
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE: Evaluate nozde to shell welded joirns in BSCs and IIAMs for the 60.5 nozzles usingan altemative design to the full penetration butt weld.
METHOD: Hand calculafions are used to determine the weld stresses from the morr€nts and forcesobtained from the BSC and IIAM FE analvses.
ASSI,JMPTIONS: N/A
IMUTS: LIGO project druwing V049-4-001 - Beam Splitter Chamb€r.LIGO project drawing VOf9-4-002 - Horizontal Access ModuleCalc. No. V049-l-066, Strucnral Design CriteriaCaIc. No. V049-1-022. BSC- FE Analvsis of Lower Section V049-1-039. IIAM FE Analysis
REFERENCES: SCeINPUTS
CAJ,CULATIONS : (SEE ATTACHED)
CONCLUSIONS: The nozde to shell welds shown in this calculaion have tle strength requtred toresist the discontinuity forces cornputed in the FE analysis. The calculation resultswere verfied by b€nd te$s rhat simulated the proposed configuration oftheconnestion.
NOTES: See the attacbment to tlis calculation for sketches ofthe revised nozzle to shell weldcooaection.
Revision No. 0Doc. No. V049-l-l0ZPage 1 of3l
PROCESS SYSTEMS INTERNATIONAL. INC.WESTBOROUGE.MA
ENGINEERINGCALCULATIONS
NO: V04$1-107Rev.Nc 0PAGE 2 OF 31
PROJECT: LIGO VACIJI,M EQUIPMENT PROJECT NO: V59049
CALCIILATION TITLE: Welds for!10.5' Nozzb ro SheI Joints
TABLE OF CONTENTS
BSC - Beam Splitter Chamber
Review of Nozzle Welds
Stress Contour Plots
J
+
IMAGES-3D Finite Element Model
Plate Stresses
Amlytical RwiewPartial Penetration Weldl/4" stirch Fiilet weldl/8" Partial Penetration Weld3/16" Stitch FiIIa Weld
FIAM - Horizontal Accrss Module
912l 4l 5
Rwiew of Nozzle Welds
Stress Contour Plots
IMAGES-3D Finite Element Model
Plate Stresses
Analytical Reviewl/8" Partial Penetration Weld3/16" Stitch Fillet Weld
Review of Connection Bend Tests
Attaclnnent 'A'
Welded Joints at Nozde to Shell ConectionsWelded Joint Connection DetailsBend Test Procedure
l 8
l 9
22
24
262727
29
A-lA-2A4
Revision No. 0Doo. No. V049-l-107Page 2 of3l
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Rwision No. 0Doo. No. Y049-1-107Page 3 of3l
Slgn conventlon for Ptate Loads/t nlt Lctrgth
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d ^ Y t t ; L t ' ^ t .
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/ LIGOPROJECT
Phil Fedand
'/.Ray Ciatto lL)n
Wetded Joints at Nozzle to Shell Connections
August2, 1996
Doc. No. V049-I-85
To:
Fron:
Subject:
Date:
A modified weldedjoint for the 6O.5 in nozzle to shell connection has been designed for theBSC and HAM. The joint will consist of a partial penetratio,n weld on the inside and anhtermittent filet weld on the outside as slrown on the attached sketches which are iacluded inthe supporting calculation for the modifted joint.
I request that beod tests of tlis weld coofiguration be performed; these are necessary to qualify
the connection. The requirernents for tlese bend tests are also attached. So that we maycompute the r1axi111um bending moment, q/e should note the m&dmum force applied by the tastmachine.
Please call ifyou have aoy quesrions on tle weld tests.
Rich BagleyDave EversRoberto Than
Dave McWilliams Tom StarrPaul Hendrv Stu Motew
Dick CurtisWalt Bilynsky
Revision No. 0Doc. No. V049-l-107Page A-l of5
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IW
PROCESS SYSTEMS INTERNATIONAL, INC.WESTBOROUGH, MA
ENGTNEERINGCALCULATIONS
NO: V049-l-039PAGE 1OF /7
REV. DEO # DATE BY: CIIECK TITLE: HAM Finite Element Analvsis0 O t 2 g lL/ m,ft- ..,{ /n ,1DO-
BY: Kvle Martini DEPT,:744
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. Evaluate the horizontal access modu le (HAM)
METHOD: Finite element method and hand calculations.
ASSUMPTIONS: See attached.
INPUTS: LIGO project drawings and sketches.Shell thickness = 0.5 in, 60 in nozzle thickness = .5 in, head thickness:0.375 inThickness of other nozzies = 0.125 in, saddle wear plate thickness:0.75 in,Thickness of saddle and stiffeners : 0.5 in. baseolate thickness : I .0 in
D a c , E - l e / 9 ' / ' e C C / - / t 4 l / E t 7 2 t . . 7 ' ' D € ! ' 1 ^ ) 4 a / t F l z / - 4 . -
REFERENCES: 1. ASME Boiler & Pressure Vessel Code, Section VIII, Pressure Vessels,Div. 1 and Div. 2.
2. IMAGES 3D, Version 3.0, R. L. Cloud & Associates3. Hilti Concrete Fastener Catolos
CALCULATIONS: (SEE AflACHED)
CONCLUSIONS: Stress are within the limits of the ASME Code, Section VIII ,Div.2.
NOTES: Computer files are HAM6.*
Rwision No. 0Doc. No. V049'1439Paee I of 19
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PROCESS SYSTEMS INTERNATIONAL, INC,WESTBOROUGH, MA
ENGINEERINGCALCULATIONS
NO: V049-1-041PAGE 1 OF 6
REV. DEO # DATE BY: CHECK TITLE: HAM Buckling Analysis0 o l z 8 4f2 I<,D (--
BY: Kvle Mamni DEPT-:744
PROJECT: LIGO Vacuum Equipment PROJECTNO: V59049
PURPOSE:. Evaluate the horizontal access modu I e (HAM) for buckling modes.
METHOD: Finite element method and hand calculation.
ASSUMPTIONS: See attached.
INPUTS: LIGO project drawings and sketches.Shell thickness = 0.5 in, 60 in nozzle thickness = 0.5 in, head thickness = 0.375 inThickness of other nozzles: 0.125 in, saddle wear plate thickness = 0.75 iqThickness of saddle and stiffeners = 0.5 in. basenlate thickness: 1.0 in
REFERENCES: NASTRAN Finite Element ProgramDae- . ,< ,Jo , /a f * - / - dA c , L /44 y 'ne . r ! ,2a , ; JrAut tT, Zf . r , l , f , r '4a ' 4
CALCULATIONS: (SEE ATTACHED)
CONCLUSIONS: The minimum factor of safety against elastic buckling for vacuum loadingis 3.58.
NOTES:
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-
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oir
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In--!r "
' .:-,-. 'J ii'7:1'
a
R'z,t DD o t , N t y ' o r ' 7 ' t -
P - - > - a z /
!
--fo ,( -" tVa/r'"
Ra "D o t , t U o .
F . 4
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6 ,''" 6
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ENGINEERINGCALCULATIONS
NO: Vo4?-r-d73AGE l OFZE_
-Gb." Ff D HE.AD / N,ZZLE DE$
,-traeeeeeeeeeeeeeee�E. HAtl
l@!@f: Lte6 PROJECTNO: V€QDaq
INPUTS: -St-AdcfdFJ.-
EESr.gr; ..lr:iii€ril. " FFi Dcc, .".,6. yo.4c-f;-z-l
REFERENCES: LQc, No,D o . l r J o , ( o v 9 - t - a a
vo49-FL- ' l .36: L ' /a ' . j t /Aa .s ' tn ' Fe ;"^ tr z,,cr, 4s r , r,/ leFsat,
CAI,CULATIONS: (SEE ATTACHED)
t* 111 ggttlAh^ {J.6 \^/ r-I-H
T u s r a ' z
fzi; ! t r--.
D,' .z n- = 6 D . 2 ) -
!,L'€ r € 4
/ a - " r t c - . a D : 6 t . i "
nlASu=- oF Uoui-e.urs
L - SeoPe-z. - DragrGU OtuT€At4.s. - lvLoog*-4. - ConPeEse .S,s-3, - lr.,Por DlrA6, - farrcAaSS \t,f i3 - OuTP,Jf
Pnsa
?
4
REVOv04+r-073Pa�ge2 of29
o o o
.{ et all
l - ScoPe.:
Qult,rl -l$€
llequtAE14 E}JT5PaoPoseo Ar.roVo41-PL- 73
bo', Htv Cov,a- _�ll
ASHE @ -6,4*-Tta Noazr€- Lai4or AS PSICrsrottz- l'f661rifr /et- Doc- No.
o o o' . t 0 0
6 t6 |a l
z.- DEsrar-l CruulvA
Ps*r = l4.Fl FslJ-= 40c"F
€ , - M o o E ! :
. N t
- N Z
f i ' 6 '
6 , - o -(-. lsSl?6
-
@.- ?o'
G . t € . 7 s '
O < ' ? 7 c "
REVOvM9-1473Pag€ 3 of29
- N 3
4.- CoHPil.Es> S,6g llrPur D,ar.{:
' Xltearnu,
* Fr-o Heao r sAz46 Soqu Hrcu
- Noz=rES (4.-\: 5A 246 '3o4L l-{r6r't
49 = l { .Y Ps t
REVOv049-l-073Page 4 of29
F F F
I I I
o o o
DEsrau JEnP = 4oo"tc
LoNC" S'=av-r X- tet- Slaaur-ass ,'. N6' x-RnY
Heao /Saau- Se,cr-l X-R.qY- Spor Pe.e- U ll - rl (b) Jlea t
-Lu = aO- 2.5
Citowr.t lr*raarqar- Rtorr.lg = @,?-€'
. Kuuc<la lr.iraArtAr- RAcr..rs < 3.?\t'
' FoR-F4 tx.lg Asrsvr*u cq --o'
. SrilArcot+r F,auqa- l '
. -TlrcKN
Ei5 =. . 2S6 n
Foe [\o aatgs:
. lP z '7.€' (A-J
. -h+,cruESS
= .ZS^ (n-.)
I$ , : o ,o o .
Na'. @"' t'5"
\Jo : @.: 2n4o
DrSrAxrc.6. a
F = 6 ' '
G' /S, 75 '
ll = rs1 7o-'
o o o
d d n
@
Ccrrpirf fux ao" F* b //e,aO /rt'CLu'or*c- Nazan"es;I + Z AAe , rxcr+e.C Tt Ver,fY 4oHpuAtJc,;
16 Asr ' ta w , t l lz EorrroxJ l r"reirrorruc 4 9-?Aooe.uon
Nora I Awl-vsrs /R.esuers troc Noa.zr€- r4 3lS S Y l',1 11l=-r&r g4 L.-Y I o.gu nc-,{ i- TaNoa*g rL Z.
R.EVOv049-r-073P&gc 5 of 29
TABI.B OF COIfTENTS
Pressure SumnaryweighE sunrnary
1
3456
J- f
z 5
Nozzle SumnaryThickness Sumnary50 II F&D HAM HEADN1-CENTERN2-RIGHT
Totsal Pages In This Report
REVOv049-l-073Page 6 of29
3 _L2 -L996
Pressure Summarv
Pressure srntrnary for pressure channber 1
t - t -| 60 ' F&D xBU naAD
I Dr. Nr -cBlrTBR
I n 2 2 - * r G E r
I r !3 N3-trBrT
6 7 . 2 | 6 7 - 2 | 2 0 . 6 | 1 . 0 0 0 |
7 e . o I r e . 0 | 1 5 . 5 | 1 . 0 0 0 I
? e . o | 7 e . o I 1 5 . 3 | 1 . o o o I
? e - o I 7 e - o I 1 s - t l r - o o o I
ocs-5 5
l{Dx? Bxe[PtloD o.
(ateg F) Bt .es6 Reduct io!
| r Io t !pp1 ic lb le
l nor ! !9 l , i cab l€
I Nor app l i cab le
l n o ! . p p l i c a b r e
| ( rD ) I
I o . o D o I
I o , o o o II o . o o o I
I o . o o o I
t_ t
l N o z z l e I t I r i A r !
I sraru6 | de6ien I
I (DG--4s) | (d€E F) | (pBi)
r i A D I P e l l j c - 9 9
l € x t e l n a r I R a ! i o
{ p E i ) I { p E i ) |
| | o . o I
I o k I o . o I
I " k I o . o II o k | 0 . 0 |l _ t _ l _t_t_ l
Vesse1 MAWP hots & corroded is 67.2 psi e 0 degrees F.
Vessel MAP new a cold is 67.2 psi @ 70 degrees F.
Vessel al lowable external pressure j-s 15.31 psi @ 400 degrees F.
Eydrotest pressure calculat.iou based on lBtfP
= 1.5* (MAWP + Operating r, iguid Headl*1 = 100.8 psi
Vessel hydrotest pressure is 100.8 psi.
I{ote: vessel IIIAP rating aot' val id unless hvdrotest pressure based on lllAp -
REVOv049-1-073Page 7 of29
3 - L 2 . L 9 9 6
Weiqht Sumarv
c o n p o l e D t - - - - - - - - { € i g h t ( t b s ) c o n l f i b u r e d b y v e s E e l B t e h € D r 6
Ie ta l l teEa l Tray€ Pached l l su l L i l i l g r ip iEg lJaddcr R inE! OpeE te6 ! ro2z le
l re r Cor r & Eup Beata & p la ! & i t i6c r , iEu id t iqu id & f tg
6 0 , f & d h a b h e r ! ? 3 2 7 3 0 o O o o O o O i 4 r 2 4
2 f 1 2 7 3 0 0 0 o 0 0 D o ? 4 t 2 4
ve€€€ l ope la t i !9 se ig l l t , co l roa ted : 29? 1b6
vesse l eopty ,e tgb t , cor .ode i t j 291 tb6
v€ase l eoPty fe igh i , Ee* : 297 1b6
v e s s e l E o a t s e i g b c , l e r : 1 , 0 3 8 I b 6
vessel center of aravity location (frotn rigiht weld seam)
Vessel- l i f t weight. new:Center of gravity to seam:
297 l ]bs/ - e r a n
REVOv049-1-073Page 8 of29
3 . L 2 . L 9 9 6
Nozzle Sulmarv
! {ozz}€ oD to Req ! ! } lon b Reg t oaer t cor r aa /a !
E l r k ( i ! ) ( i D ) ( i a l a l ? A 2 ? ( 1 r l ( i ! ) { i [ ) ( i ! ] ( + )
D 1 a . o o o . 2 5 o o 0 . 1 4 2 ? f y o . 2 5 o o 0 . 1 t ? 3 0 . 2 5 0 0 0 . o 0 o o 1 0 0 . 5
n Z a , O O 0 - 2 5 0 0 0 - 1 4 2 7 f y 0 . 2 5 0 0 C - 1 9 3 7 0 - 2 5 0 0 0 . 0 0 0 0 1 0 4 . 3
n 3 A - O O 0 - 2 5 0 0 0 . 1 4 2 7 y y O . 2 5 O O 0 . 1 9 3 ? 0 - 2 s 0 0 0 . 0 0 0 0 1 o { - 3
tn - r]ozzl-e thicknessReq tn - nozz\e thickness required per UG-45/15Nom t - vessel wal1 thicknessReq t - required wessel wall- thickness due to pressure + corr per UG-37User ts - 1ocal vessel wal1 thickness (near opening)Aa - area awaj.lable per uG-37, governing conditionAr - area requj-red per rJe-37, governing conditionCorr - corrosion allowance on nozzle id.
REVOv049-r{?3Pzge9 of29
3 . t 2 - 1 9 9 6
Ttriclroess Surmar:f
Ir€Egrh D e f l e c t
s r r e 6 6 ( l D )( i ! ) ( i D ) I L o a d
5 0 i t i d h a [ h e a d l 0 , . 2 5 0 0 0 , 2 5 0 0 0 . 4 5
Nom tReq tE
Load:internalexternalwindsei smic
vessel wall thicknessrequired vessel wall Lhickness due to governing loadinglongitudinal seam joint efficiency
- circ stress due !o internal pressure governs- excernal pressure governs- combined long stress due to SrATUS + wind governs- combined lonq stress due to STATUS + seismic cloverns
RDVOv049-l-073Page l0 of29
3 -L2 .L995
5ON F&D EAM EEJAD
ASIIIB Section VIfI Division 1. 1992 Bdition. A93 Addenda
Component: F&D headMaterial specif icat ion: SA 240 304L HIGH
Corrosion allowance: fnner C = 0 Outer= 0
PITIIT is noL Derformed
Radiography: Category A j ointsHead to shel1 seam
Seamless NO x-Rayspot t w-11 (b) type
corc = 272 .9c o r r = 8 8 . 8 9
B = 5 0 0 4 . 1
Estinated weight :capacity :
ID = 50 .25 c rown L =
Straights flange = 1
A = . l -25r l (Ro,/ t )= , L z . / \ b u . 5 / U . . 1 5 ,= 0 . 0 0 0 5 1 7
From table HA-3 r
pa= B,r (Ro/t )= 5 0 0 4 . r / ( 6 0 . s / o - 2 s )= 2 0 . 6 7 8 t _ p s i
60 -25 knuck l -e r = 3 .75 E = .25
n e w = 2 7 2 . 9n e w = 8 8 . 8 9
' l h
US ga
in (min)
forminq allowance = 0
IrtAP: (Iilew & at. 70 deg F) AtrE endix 1-4(d) Ea 3
P = 2 * S * E * t / ( I r * M + 0 . 2 * t ) - P s= 2 *16700*0 .85*O .25 / (60 .25* r . ' 7521 + 0 . 2 *O .25 ) -= 61 .20225 osi
MAflP: (Corroded & at 0 deg F) Appendix 1-4 (d) Bq 3
P = 2 * S * E * t / ( I r * M + 0 . 2 * t ) - p s= 2 * 1 6 7 0 0 * 0 . g S * O . 2 5 / ( 6 0 . 2 5 * 1 . . 7 5 2 I + O . Z * O . 2 5 ) -= b I . z U z Z 5 r ) S ] -
Maxj-mn Allorable hcternal Pressure: (Corroded @ 400 degr F)
l-n
Check lhe Maximum Ext,ernal Pressure: UG-33 (a) (1) & App. 1-4(d)
P e = 2 * S * E : t t l ( ( M * L o - g * ( M - 0 . 2 ) ) * ! . 5 7 )= 2 * 1 4 7 0 0 * 1 t O - 2 5 / ( ( 1 . 7 5 2 1 * 6 0 . 5 _ 0 - 2 5 * ( L . 7 5 2 1 - O . 2 ) ) * L . 5 7 )= 41,.67247 ps!
The maxirmlm al-l-owable external pressure is 20.6781- psi.
REVOv049-r473Page ll of29
3 . L 2 . L 9 9 6
N1-CETiITER
Opening n1 Reinforcement Calculations Per IIG-37
LocaEed on: 60 II F&D HAM I{EADUser input vessel thickness: .25 inLiguid staEic head included: 0 psiFlange description: Not instaLled
Nozzle materiaL specif i-cation: SA 240 304L HIGH
Nozzle orientat ion: 0 degreesEnd of rLozzle to datum l ine: L4.53 inNozzle calculated as hi l ls ide: yesProjection outside vessel Lpr: 3.527 ln
tn ->
tswl-->< - d - >
-t
< - R - r l
c o r r o s i o n a l l o w = 0 i nnoz thick neirJ tn= .25 innozz:-e id. new d= 7.5 inf i l let wel-d tw1 = .25 ingroove weld tw2 = .1875 in
To head cent.er R= 8 in
I Reinforcement calculations For Nozzle ItlAvIP
timits of reinf orcement IIG-40
Paral le1 to the wessel wa1l d = 7.567 inNormal tso che wessel waII out.s ide 2.5* ( tn-Cn) + te = .625 inNormal Eo lhe vessel waII inside 2.5* ( tn-Cn-C) = .625 in
Deterui[at ion of ehord Lenqth
'Itret al- = Arccos ( (Lo + P11 /Rm)= A rcCos ( (8 + 3 -75 ) / 60 .3213s )= 7 8 . 7 6 7 9 7
Theta2 = Arccos ( (i,o - Rn) ,/Rm)= A r c c o s ( ( 8 - 3 . 7 5 ) / 6 0 . 3 2 1 3 s )= 8s .96O29
d = 2*Rm*Sin( (Thetaz - Thetal) , /2)= 2 * 6 0 . 3 2 1 3 5 * S i n ( ( 8 5 . 9 6 0 2 9 - 7 8 . 7 6 7 9 7 ) / 2 )= 7 . 5 6 7 t n
Nozzle resuired thickness
941 = P*Rn / (Sn*E - 0 .5 *P)= 79 .06L4L*3 .75 / (L6700*1 - 0 -6 *79 .O614 t )= 0 . 0 1 7 8 i n
REVOv04t1{73P�age12 oizg
3 - 1 2 - 1 9 9 6
N1-EEIITER
Required thickness tr from ItG-37 (a) (1)
! r = P * L * M / ( 2 * S * E - 0 . 2 * P )= 7 9 . O 6 a 4 a * 6 0 . 2 5 * I / ( 2 * 1 5 7 0 0 * 1 - O . 2 * 1 9 . 0 6 1 4 1 )= 0 -L427 in
Area resuired
Al lowable slresses: Sn = L6700, Sv = 15700, psi
f r1 = lesser of L or Sn/Sv so fr1 =1fr2 = lesser of L or Sn/Sv so fr2 =1
A = d * t r *F + 2 * tn * t r *F* 11 _ f r1 )= 7 . 5 6 7 * 0 . 1 _ 4 2 7 * 1 _ + 2 * 0 . 2 5 * O . a 4 2 7 * l * ( 1 - 1 )= 1 . 0 7 9 8 i n ^ 2
Area avai1ab1e
A1 = larger of the fol lowing = .812 in^2
= d * (E1* t_F* t r ) _ 2 *gn* (E1* t_F* t r ) * (1 - f r1 )= 7 - 5 6 7 * ( 1 * 0 . 2 5 - 1 * 0 . ! 4 2 7 ] , - 2 * O . 2 5 * ( 1 * 0 . 2 5 - L * 0 . L 4 2 7 ) * ( 1 - a )= -81-2 in^2
= 2 r ( ( t+ tn ) * (81* t -F * t , r ) - 2 * tn * (E1* t -F * t . r ) * (1 - f r l )= 2 * ( 0 . 2 5 + O . 2 5 ) * ( 1 * 0 . 2 5 - 1 * 0 . 1 4 2 7 ) - 2 * 0 . 2 5 * ( L * 0 . 2 5 - 1 * 0 . 1 - 4 2 7 ) * ( 1 - - ! )= . LO7 !r t^ 2
A2 = srnaffer of the following
= 5r ( tn - t rn) * fyz*L= 5 * ( 0 . 2 5 - 0 . 0 1 7 8 ) * 1 - * 0 , 2 5= .29 j-rl^2
= 5 * ( t n - t r n ) * f r2 * tn= 5 * { 0 . 2 5 - 0 . 0 1 7 8 ) * 1 * 6 . 2 5= .29 i r :^2
A41 = Leg^ 2 * fr2= o . 2 5 ^ 2 t , 1 _ = . 0 5 3 i n ^ 2
= O .29 i-r:^ 2
A r e a - A 1 + A 2 + A 4 1= 0 . 8 1 2 + 0 . 2 9 + 0 . 0 6 3= 1 .1 -65 i n^2
As Area > A the reinforcement is adequate for MAWP = 79.06!41 at 0 Deg F
Reinforcement check in the p1ane para]-lel to the long. axis
Area reouired
I A = d * t r * F + 2 * t n * t r * F * ( 1 - f r 1 )
REVOv04+l{73Page 13 of29
3 . L 2 . L 9 9 6
N1-CENTER
= 7 . 5 * 0 . 1 , 4 2 7 * 7 + 2 * 0 . 2 5 * O . L 4 2 - 1 * ! * ( t _ 1 )= r .07025 j . I r^ 2
Area a-rrailable
41 = larger of Lhe fol lowing = .805 in^z
= d * (E1* t -F * t r ) - 2 * tn * (E l * t -F * t . r ) * {1 - f r1 )= 7 . 5 * ( 1 * 0 . 2 5 - 1 * 0 . L 4 2 7 ) - 2 * 0 . 2 5 * ( l _ * 0 . 2 5 - 1 * 0 . L 4 2 7 ) * 1 ] - - 1 1= . 8 0 5 i n ^ 2
= 2 * ( t + t n ) * ( 8 1 * t - F * E r ) - 2 ' t t n * ( E 1 * t - F * t r ) * ( 1 - f r 1 )= 2 * ( 0 . 2 5 + 0 . 2 5 ) * ( 1 r r 0 . 2 5 - 1 * 0 . L 4 2 7 ) - 2 * O . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . L 4 2 7 ) * 1 1 - a )= .1-07 in^2
A r e a = A L + A 2 + A 4 1= 0 . 8 0 5 + 0 . 2 9 + 0 . 0 5 3= 1 . 1 _ 5 8 i n ^ 2
As Area > A Che reinforcement is adequate for MAIIP = 79.O6f4f af 0 Deg F
Check the welds - Frm [ttf-15(d):
tm in = l esse r o f 0 .75 o r t n o r t , tm in = 0 .25 i nt l - or t ,2 (min) = lesser of 0 .25 or 0 .7*tmin, t .1 (nin) = 0.1-75 int l ( a c t u a l ) = 0 . 7 * L e g = 0 . 7 * 0 . 2 5 = 0 . 1 7 5 i nt2 (accua l ) = 0 .1875 i nt 1 + t 2 = 0 . 3 5 2 5 > = 1 . 2 5 * t m i n
The weld sizes for t1 and t2 are sat isfactory.
ItG-45 Nozzle Neck thickness &eck
Wal1 thickness per UG-45 (a) :vlal l thickness per UC-45(b) (1)Wal-L thickness per UG-16 (b) :Std pipe wal- l per UG-as (b) (a) :T'he greater of Er2 or tr3:Ttre lesser of tr4 or t.r5 :
E r 1 = 0 . 0 1 7 8 i n ( E = 1 ): Xr2 = 0.L427 in
t r 3 = 0 . 0 5 2 5 i nt r 4 = 0 . 2 8 1 7 5 i nt r5 = 0 -1427 lnEr6 = 0 .J -427 in
Req'd per UG-45 is the larger of t r1 or t r6 = O.f427 in
Available nozzl-e wa1I thickness new, tn = 0.25 in
The nozzle neck tshickness is adequate for MAWP.
A]-]-owable stresses in joirts UG-45tc) and ftvf-15 (c)
Groove weld in tension = O.74*L61Q0 = i -2358 psiNozz le waL l i - n shear = O .7*L57OO = 11690 ps ihne r f i l l e t we ld i n shear = o .49*L67O0 = 8L83 os i
St'rength of wel-ded ioints:
3 . L 2 . L 9 9 6 REVOv04+l-073P,;ge 14 of29
N1-CENItsR
(1) Inner f i I let weld in shear(P i /2 ) *Nozz l -e O .D . *Leg*S i = 1 .57*8*0 .25*8183 = 25694 .62 l b f
(3) Nozzle walL in shear( P i / 2 ) * M e a n n o z z L e d i a . * t n * S n = L . 5 7 * 7 . 7 5 * 0 . 2 5 * L ! 5 9 0 = 3 5 5 5 9 . 5 2 L b f
(4) Groowe weld in tension( P i / 2 7 * y 1 o " r 1 e O . D . * t w * S g = 1 . 5 7 * 8 * 0 . 1 8 7 5 * l - 2 3 5 8 = 2 9 1 0 3 . 0 9 l b f
Ioadinq on we1ds Der UCI-41 (b) (1)
W = ( a - ( d - 2 * t n ) * ( E 1 * t - F * t r ) ) * S w= ( 1 . 0 7 9 8 - ( 7 . 5 6 7 - 2 * Q . 2 5 ' ) * ( 1 * 0 . 2 5 - 7 - * 0 . t 4 2 7 ) ) * 1 6 7 0 0= s 3 5 9 . 2 3 2 l b f
WL-1 = (A2 + A5 + A41- + A42)*5o'= ( 0 . 2 9 + 0 + 0 . 0 5 3 + 0 ) * 1 6 7 0 0= 5 8 9 5 . 1 l b f
W2-2 = (A2 + A3 + A41 + A43 + 2 * tn * t * f r1 ) *Sv= ( 0 . 2 9 + 0 + 0 . 0 5 3 + 0 + 2 * 0 . 2 5 * 0 . 2 5 * 1 ) * 1 5 7 0 0= 7982 .5 l b f
I" ,oad for path 1-1 lesser of w or W1-1 = 5369.232 lbfPath l - -1 Thru (1) a (3) = 25694.62 + 35559.52 = 61254. l -4 1bfPath 1-1 is strongrer than w so i t is acceptable per UG-41 (b)(2).
Load for paE}f 2-2 lesser of w or w2-2 = 5369.232 lbfPaE}] 2-2 hTLru (1) , @) = 25694.62 + 29L03 -O9 = 54797.71 lbfPath 2-2 is stronger than w so i t is acceptable per UG-41 (b)(2).
Reinforcenent Caleulations For Nozzle IqAP
LitrLits of reinforcenent UG-4O
Paraf le l to tshe wessel waLf d = 7.557 i , r rNorma1 to the vessel wal1 out,s ide 2.5* ( tn-Cn) + te = .625 inNormal to the vessel wa11 inside 2.5* (Ln-Cn-C) = .525 in
Det eruinat ion of flrcrd Lencrth
Thetal = Arccos ( (Lo + R-rI) /Rm)= A r c C o s ( ( 8 + 3 . 7 s ) / 6 0 . 3 2 1 3 5 )= 7 8 . 7 6 7 9 1
T'heta2 = ArcCos ( (r,o - Rn) /Rm)= A r c C o s ( ( 8 - 3 . 7 5 ) / 6 0 . 3 2 1 - 3 5 )= 85 .96Q29
d = 2*Rm*Sin( (Theta2 - Ttretal) /2)= 2 * 6 0 . 3 2 1 3 5 * S i n ( ( 8 5 . 9 5 0 2 9 - 7 8 . 7 6 7 9 7 ) / 2 1- ' 7 1 C ' 7 : n
REVOv049-14?3Page 15 of29
3 -L2 .L996
N1_CN\ITER
Nozzle required Lhickness
t rn = P*Rn / (Sn*E - 0 .5 *P)= 7 9 . 0 6 1 4 1 * 3 . 7 5 / ( 1 6 7 0 0 * 1 - 0 . 6 * 7 9 . 0 6 1 4 1 )= 0 . 0 1 - 7 8 i n
Recuired thickness tr from ItG-37 (a) (1)
t r= P*L*M/ (2 *S*E - 0 .2 *P)= 7 9 . 0 5 1 4 1 * 6 A . 2 5 * L / ( 2 * a 6 7 0 0 * 7 - 0 - 2 * 7 9 . 0 5 L 4 1 )= 0 . 1 4 2 7 i n
Area reouired
Al l -owable sEresses: Sn = r57O0, Sv = 16700, psi
f r1 = lesser of 1 or Sn/Sv so fr1 =1fr2 = lesser of 1- or Sn/Sv so fr2 =1
A = f l*91*p + 2*tsn*tr*F* (1 - f r1)= 7 . 5 6 7 * 0 . L 4 2 7 * ! + 2 * 0 . 2 5 * 0 . a 4 2 7 * 1 * ( 1 _ 1 )= I .O798 i -r l^ 2
Area available
A1 = larger of the foll-owing = -8r2 j.n^ 2
= d * (E l * t -F * t r ) - 2 * tn * (E l * t -F * t r ) * (1 - f r1 )= 7 . 5 6 7 * ( 1 - * 0 . 2 5 - L * 0 . 1 4 2 7 ) - 2 * 0 . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . 1 4 2 7 ) * ( 1 - ! )= .8L2 in^Z
= 2* ( t+ tn ) * (81*E-F* t r ) - 2 * tn * (E1* t -F * t . r ) * (1 - f r1 )= 2 * ( 0 . 2 5 + 0 . 2 5 \ * ( 1 * 0 . 2 5 - 1 * 0 . ! 4 2 7 \ - 2 * O . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . L 4 2 7 ) * ( f - L )= . ! 07 i n^Z
A2 = smaller of the following = 0.29 j-'j-^ 2
= 5 * ( t n - t r n ) * f r2 * t= 5 * ( 0 . 2 5 - O . 0 1 - 7 8 ) * 1 * 0 . 2 5= .29 i -n^2
= 5 * ( t n - ! r n ) * f r2 *En= 5 * ( 0 . 2 5 - O . 0 1 7 8 ) * 1 * 0 . 2 5= .29 i t ^2
A4l = Leg^ 2* fTz= o . 2 5 ^ 2 * I = . 0 6 3 i n ^ 2
Area = Al- + A2 + A41= 0 . 8 1 2 + 0 . 2 9 + 0 . 0 5 3= 1 . 1 6 5 i n ^ 2
I As Area > A the reinforcement is adequate for MAP = 79.06141 at 70 Deg F
REVOv049-l-073Page 16 of29
3 . L 2 . L 9 9 6
N1-CENTER
L Reinforcement check in the plane paral]-el to the long. axisIt
A.rea reou1rao
A = d * t r *F + 2 * tn * t r *F* (1 _ f r1 )= 7 . 5 * O . ! 4 2 7 * r + 2 * 0 . 2 5 * 0 . L 4 2 7 * 7 _ * ( 1 _ 1 )= 7.07025 j - I :^2
Area availabl-e
A1 = l-arger of the following = .805 in^2
= d * (E1* t -F * ! r ) - 2 * tn * (E1*L -F* t r ) * (1 - f r1 )= 7 . 5 * ( 1 * 0 . 2 5 - t - * 0 . ] - 4 2 7 ) - 2 * 0 . 2 5 * ( l _ * 0 . 2 5 - 1 * 0 . 1 4 2 7 ) * ( 7 - L )= . 8 0 5 i n ^ 2
= 2 * ( t+ tn ) * (E1* t -F * t r ) - 2 * tn * (B1* t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 2 5 + O . 2 5 ) * ( 1 * 0 . 2 5 _ 1 * O . 1 4 2 7 \ - 2 * 0 . 2 5 * ( 1 * 0 . 2 5 _ 1 * 0 . L 4 2 7 ) * ( a - A )= , 1 0 7 i n ^ 2
Area = A1 +A2 + A4l-= 0 . 8 0 5 + O . 2 9 + 0 . 0 6 3= 1 . 1 5 8 i n ^ 2
As Area > A the reinforcement is adequate for MAP = 79.06141 at 70 Deg F
Check the welds - Frm Uw-15 (d):
tm in = l esse r o f 0 .75 o r t n o r t , tm i .n = 0 .25 i nt ,1 or t2 (min) = lesser of 0 .25 or 0 .7*t f iL in, t ] . (min) = o .175 int 1 ( a c t u a l ) = o . 7 * I J e g = 0 . 7 * 0 . 2 5 = 0 . 1 7 5 i nt 2 ( a c t u a l ) = 0 . 1 8 7 5 i nE 7 + E 2 = O . 3 5 2 5 > = 1 . 2 5 * E m i n
The weld sizes for t ,1 and t2 are sat isfactory.
UC9-45 Nozzle Neck Thickness Check
wa l I Eh i ckness pe r UG-45 (a ) : t r 1 = 0 .0L78 i n (E = 1 )WaI1 thickness per UG-a5 (b) (1) : Lr2 = 0. t427 j - , tLWaI1 th i ckness pe r UG-15 (b ) : L r3 = 0 .0525 i nS td p ipe wa1 l pe r UG-45 (b ) (4 ) : t r 4 = 0 .28175 inThe greater of Lr2 or t r3: t r5 = 0 .1427 LnThe lesse r o f t r 4 o r t r5 : t r 5 = 0 . !427 i n
Req'd per UG-45 is the larger of t r1 or t r6 = 0.1427 in
Avail-able rLozz)-e wal- l- t.hickness new, tn = 0.25 in
The nozzle neck thickness is adequate for MAP.
A1ldwal)le stresses in ioints IE-45(c) and Uw-15(c)
REVOv049-l-073Page 17 ol29
3 _L2 _L996
N1-CENTM,
Groove weld in tension = O-74*7.6700 = 12358 psiNozz le wa l l i n shea r = 0 .7 *16700 = 1 -1 ,590 ps irnner f i l let weld in shear = 0.49*!6700 = 8183 psi
Strengrtsh of welded joints:
(1) Imer f i l Iet weld in sbear(P i /21 *ySs r r l e O .D . *Leg*S i = 1 .57*8*0 .25*8183 = 25694 .52 1b f
(3) Nozzle wa11 in shear(P i /2 ) *Uean t ] ; ozz le d ia . * tn *Sn = ! . 57*7 .75*0 .25*L1690 = 35559 .52 Ib f
(4) Groove weld in tension( P i / 2 1 * 1 1 o " r 1 e O . D . * t w * S g = 1 . 5 7 * 8 * 0 . 1 - 8 7 5 * 1 2 3 5 8 = 2 9 1 0 3 . 0 9 l b f
Loading on relds per UG-41 (b) (1)
W = ( e - ( d - 2 * t n ) * ( E 1 * t - F * t r ) ) * S v= ( 1 . 0 7 9 8 - ( 7 . 5 6 7 - 2 * O . 2 5 , * ( 1 * 0 . 2 5 - 1 - * 0 . A 4 2 7 ) , * 1 5 7 0 0= s369 -232 tbf
W1-1 = (A2 + A5 + A41 + A42) *go'= ( 0 . 2 9 + 0 + 0 . 0 5 3 + 0 ) * 1 5 7 0 0= 5 8 9 5 . 1 - 1 b f
w2-2 = (A2 + A3 + A41 + A43 + 2*tn*t* fr l ) *Sv= ( O . 2 9 + 0 + 0 . 0 6 3 + 0 + 2 * 0 . 2 5 * 0 . 2 5 * 1 ) * 1 6 7 0 0= 7982 .5 1b f
Load for patsh 1-1 lesser of W or W1-1- = 5359.232 l - ,bfPa th 1 -1 rh ru (1 ) & (3 ) = 25694 .62 + 35559 .s2 = 6 t254 .14 l b fPath L-1- is stronger than w so ic is acceptable per UG-41 (b) (2).
Load for path 2-2 fesser of W or W2-2 = 5359.232 l --bfPa th 2 -2 T t r ru (1 ) , (+ ) = 25694 .52 + 29L03 .O9 = 54 '797 ' 71 l b fPath 2-2 is scronger than w so i t is accepEable per UG-41 (b)(2)-
Reinforcement ealculations for Extetrral- Pressure
timit's of reinforcement UG-40
Paral le l to the wessel waI1 d = 7.567 lnNormal to the vessel wa1l outside 2.5* ( tn-Cn) + Le = '525 inNormal to the vessel waI1 inside 2.5* ( tn-Cn-C) = .525 in
Deteminat ion of Chord I'enqth
Thet.al = Arccos ( (Lo + Rn) /RIn)= A rcCos ( (8 + : . 75 ) / 5O.34865)= 7 8 . 7 7 3 r 2
Theta2 = Arccos((Lo - Rrr) /Rm)= A rccos ( (8 - 3 .75 ) / 60 .34855)
R.EVOv049-l-073Page 18 of29
3 . L 2 . t 9 9 6
N1-CENTER
= 85.962L2
d = 2*Rm*Sin( (Theta2 - Thetal) /2)= 2 * 6 0 . 3 4 8 5 5 * S i n ( ( 8 5 . 9 6 2 L 2 - 7 8 - 7 7 3 L 2 )= 7 . 5 6 7 i n
Nozz]-e required thickness
L / D o = 3 . 5 2 7 / 8 = . 4 4 0 9From table G:From EabLe IIA-3 :
Pa= 4*B / (3 *Do l t )= 4 * 4 7 4 5 . 9 / 1 3 * I / 0 . 0 1 9 8 1 - )= 1-5 .6727 psL
Nozzle required lhickness trn =
oo/ t =A =
8 / 0 . 0 1 9 8 10 . 0 0 0 3 8 34 7 4 5 . 9
= 4 0 3 . 8 3 6 4
. 0 1 9 8 1 i n
Area required
AlLowable scresses: Sn = L47Ao, Sv - 14700,
fr l- = Iesser of L or Sn/Sv so fr1 =1fr2 = lesser of l- or Sn/Sv so fr2 =l-
psa
A = 0 . 5 * ( d * t s r * F + 2 * t n * E r * F * ( 1 - f r 1 ) )= 0 . 5 * ( 7 . 5 6 7 * O . 1 9 7 3 * 1 + 2 * 0 . 2 5 * 0 . 1 9 7 3 * 1 * ( 1 - 1 ) )= .7455 irl^ 2
Area availalrle
A.1 = larger of the following = -399 j,n-2
= d * {E1* t -F * t r ) - z * tn * (E1* t -F *L r ) * (1 - f r1 )= 7 . 5 6 7 * ( 1 * 0 . 2 5 - 1 * 0 . ! 9 7 3 ) - 2 * O . 2 5 * ( 1 * 0 . 2 5 - 1 , * 0 . 1 9 7 3 ) * ( 1 - 1 )= .399 in^2
= 2 * ( t + t s n ) * ( 8 1 * t - F * t r ) - 2 * t n * ( E 1 * t - F * C r ) * ( t - f r 1 )= 2 * ( 0 . 2 5 + 0 . 2 5 ) * ( 1 * 0 . 2 5 - 1 * 0 . 1 - 9 7 3 ) - 2 * 0 . 2 5 * ( 1 * 0 . 2 5 - L * 0 . 1 9 7 3 ) * ( 1 - 1 )= . 0 5 3 i n ^ 2
A2 = smal ler of lhe folJ-owing = 0.288 in^2
= 5 * ( t n - t r n ) * f r2 * t s= 5 * ( 0 . 2 5 - 0 . 0 1 9 8 1 ) * 1 - * 0 . 2 5= .288 !n^ 2
= 5 * { t n - t r n ) * f 1 2 * t n
= 5 * ( 0 . 2 5 - 0 . 0 L 9 8 1 - ) * t * o . 2 5= . 2 8 8 i n ^ 2
REVOv049-r{73Page 19 of29
3 - 12 .1996
N]--CENTER
A4L = Leg^2*fr2= O . 2 5 ^ 2 * L = . 0 5 3 i n ^ 2
A r e a = A 1 + A 2 + A 4 1= 0 . 3 9 9 + 0 . 2 8 8 + 0 . 0 5 3= .75 in^2
As Area > A the reinforcement is adequate for Pe - 15.58935 at 400 Deg F
Reinforcement check in the plane parallel to the ]-olrg- axis
Area reouired
A = 0 . 5 * ( d * t r * F + 2 * t n * E r * F * ( 1 _ f r 1 ) )= 0 . 5 * ( 7 . 5 * 0 . 1 - 9 7 3 * 1 + 2 * 0 . 2 5 * 0 . 1 9 7 3 * 1 * ( 1 - 1 ) )= . 7 3 9 8 7 5 i n ^ 2
Area av-ailab]-e
A1 = larger of the following = . 5 9 5 r n 2
= d* (E1* t -F * t r ) - 2 * tn * (E l * t -F * t r ) * (1 - f r1 )= 7 - 5 * ( l _ * 0 . 2 5 _ 1 * 0 . 1 9 7 3 ) _ 2 * 0 . 2 5 * ( 1 * 0 , 2 5 _ 1 * 0 . 1 9 7 3 ) * ( 1 _ 1 )- . J 9 5 l - n , l
= 2* ( t+ tn ) * (E1* t -F * t r ) - 2 *Ln* (E t * t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 2 5 + O . 2 5 ) * ( 1 * 0 . 2 5 - 1 * 0 . 1 9 7 3 ) - 2 * O . 2 5 * ( L * 0 . 2 5 - 1 * 0 . 1 9 7 3 ) * ( 1 - 1 )= . 0 5 3 i n ^ 2
A r e a = A L + A 2 + A 4 i _= 0 . 3 9 5 + 0 . 2 8 8 + 0 . 0 5 3= .7 46 in^ 2
As Area > A Lhe reinforcement is adequate
IIG-45 Nozzle Neck Thiclmess Check
Wall ehickness per UG-45 (a) : trl =WaI1 thickness per UG-as (b) (2): Er2 =Wal] tshickness per UG-r-5 (b) : tsr3 =Std pipe waI l per Uc-45 (b) (4) : t r4 =T'he greater of tr2 or tr3: tr5 =The lesser of t r4 or t rs: t r6 =
fo r Pe = 15 .58935 a t 400 Deq F
0 . 0 1 9 8 1 i n ( E = 1 )0 . 0 3 2 i n0 . 0 6 2 5 i n0 . 2 8 1 7 5 i n0 .0625 i n0 . 0 6 2 5 i n
REVOv049-l-073PrEe20 of29
Reqrd per UG-45 is the larger of t , r1 or t . r5 = 0.0525 in
Available nozzLe wal1 thickness new, tn = 0.25 in
The nozzle neck thickness is adecnrate for Pe.
3 - 1 2 - 1 9 9 6
I{2 -RIGIfT
O[rening n2 Reinforcement Calcu]-ations Per IrG-37
Located on:User input vessel thickness:Liquid static head included:Flange descript ion:
Nozzle materia] specif icat ion:
Nozzle orientat ion:End of rozzl-e to datum fine:Nozzle calcuLated as hi l ls ide:Projection outside vessel Lpr:
6OX F&D HAM HEAD.25 i r l0 ps iNot instal-led
SA 240 3O4L I{ IGH
90 degrees1 4 . 5 3 i n. r v 4
5 . 0 8 2 i n
twl-->< - d - >
v
fn ->
corrosion allovr =noz thick new tn=nozzl-e id. new d=fi I lets weld tw1 =qroove weld tw2 =
0 i n.25 in/ . 5 1 n- 1 5 l - n. 1 8 7 5 i n
< - R - > l To head center R= L5.75 in
Reinforcement Calculations For Iilozzle MAI{P
Limits of reinforcernent IIG-40
Paral le l to the vessel walI d = 7.77! lnNormal to the vessel wa1l outside 2.5* ( tn-Cn) +Norrnal to the vessef waII inside 2.5* ( tn-Cn-C)
Deter:ninat ion of grcrd Length
Tbetal = ArcCos( (Lo + Rn) /Rm)= A r c c o s ( ( 1 5 . 7 5 + 3 . 7 5 ) / 6 0 . 3 2 : - 3 5 )= 7L .L3958
t e = . 6 2 5= . 6 2 5 i n
'Ihetsa2 = Arccos ( (r,o - Rn) /Rm)= A r c C o s ( ( 1 5 . 7 5 - 3 . 7 5 ) / 6 0 . 3 2 1 3 5 )= 7 4 . 5 2 5 7 5
d = 2 *Rm*S in ( (The ta2 - The ta l ) / 2 )= 2 *60 .32135*S in ( (78 .52576 - 7L .1 -3958) /2 )= 7 . 7 7 t i n
Nozzle required thickness
t rn = P*Rn / (Sn*E - 0 .6 *P)= 79 .O5 ] -4 I *3 .75 / (75700*1 - O .6 *79 .O574r l= 0 . 0 1 7 8 i n
3 . 1 2 . 1 9 9 5
Ln
REVOv049-l-0?3Prge 2l of29
N2-RIGET
Required thich.ess tr from Uc-37(a) (1)
t r = P * L * M / ( 2 * S * E - 0 , 2 * p )= 7 9 . 0 6 r 4 L * 6 0 . 2 5 * ! / ( 2 * 1 6 1 O 0 * r - O . 2 t ' t 9 . 0 6 1 4 1 )= 0 . 1 4 2 7 i n
Area reouired
A1 lowab1e s t resses : Sn = 16700 , Sv = 15700 , ps i
f r l - = lesser of 1 or Sn/Sv so frL =1fr2 = lesser of 1 or Sn/Sv so fr2 =1
A = @*gs*p + 2 * tn * t r *F* (1 _ f r1 )= 7 . 1 7 ! * 0 . ! 4 2 7 * L + 2 * O . 2 5 * O . 1 4 2 7 * t * ( 1 _ 1 )= 1 . 1 0 8 9 i n ^ 2
Area arrailable
41 = l-arger of the following = .834 in^2
= d * (E l * t -F * t r ) - 2 * tn * (81* t -F * t r ) * (1 - f r1 )= 7 . 7 7 L * ( 1 * 0 . 2 5 - 1 * 0 . L 4 2 7 ) - 2 * O . 2 5 * { 1 * 0 . 2 5 - 1 * 0 . L 4 2 7 ) * ( a - L )= . 8 3 4 i n ^ 2
= 2 * ( t s+ tn ) * (81* t -F * t r ) - 2 * tn * (E l , * t . -F * t . r ) * (1 - f r1 )= 2 * ( O . 2 5 + 0 . 2 5 ) * ( 1 * 0 . 2 5 - 1 * 0 . 1 4 2 1 \ - 2 * O . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . 7 4 2 7 ) r < ( 1 - - I )= .L07 in^2
A2 = smal-l-er of the following
= 5* ( t n - ! r n ) * f r z * t= 5 * ( 0 . 2 5 - 0 . 0 1 7 8 ) * 1 * 9 . 2 5= - 2 9 \ I l Z
= 5* ( tn - t ' rn ) * f r2*En= 5 * ( 0 . 2 5 - 0 . 0 1 7 8 ) * 1 * 9 . 2 5= .29 in^2
A4l- = Leg^2*fr2= 0 - 2 5 ^ 2 * L = . 0 5 3 i n ^ 2
= 0 . 2 9 i n ^ 2
Area = 41 + A2 + A41-= 0 . 8 3 4 + 0 . 2 9 + 0 . 0 5 3= 1 . 1 8 7 i n ^ 2
As Area > A the reinforcement is adequate for MAWP = 79.06]-41- at 0 Deg F
Reinforcement check in the plane parallel to the long. axis
Area reamired
I A = d* t r *F + 2* tn* t r *F* ( l - f r1 )
REVOv049-t-073Page 22 of29
3 .L2 -1995
ri[2 - RIcIfr
= 7 . 5 * 0 . I 4 2 7 * t + 2 * O . 2 5 * 0 . L 4 2 7 * L * ( 1 _ 1 )= a.07025 j -r ,^ 2
Area available
Al- = larger of lhe fol lowing = .805 in^2
= d * (81* t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 7 . 5 * ( 1 * 0 . 2 5 - 1 * 0 . L 4 2 7 l - 2 * 0 . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . 1 4 2 7 ) * ( 1 - 1 )= . 8 0 5 i n ^ 2
= 2 * ( t+ t sn ) * (E l * t -F *Er ) - 2 * tn * (81*E-F* t r ) * (1 - f r1 )= 2 * ( O . 2 5 + O . 2 5 ) * ( 1 * 0 . 2 5 - 1 * O . ! 4 2 7 ) - 2 * O . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 - ] - 4 2 7 ) * ( a - a )= . L O 7 ! n ^ 2
A r e a = A 1 + A 2 + A 4 1= 0 . 8 0 5 + O - 2 9 + 0 . 0 6 3= 1 - . 1 5 8 i n ^ Z
As Area > A Ehe reinforcement is adequate for MAWP = 79.O6L4a ats 0 Deg F
Check the welds - Frm III{-16(d):
tm in = l esse r o f 0 .75 o r t n o r t , tm in = 0 .25 i nt1 o r ! 2 (m in ) = l esse r o f 0 .25 o r o .7 * tm in , t L (m in ) = 0 .175 i nt 1 ( a c t u a l - ) = 0 . 7 * I J e g = 0 . 7 * 0 . 2 5 = 0 . 1 7 5 i nt 2 ( a c t u a l ) = 0 . L 8 7 5 i nt 1 + t . 2 = 0 . 3 6 2 5 > = 1 . 2 5 * t m i n
The weld sizes for t1 and t2 are satisfactory.
UC-45 Nozzle Neck lbickness dleck
v {a1 l t h i ckness pe r UG-45{a ) : t r 1 = 0 .0178 i n (E = 1 )Wa1 l t h i ckness pe r UG-45(b ) (1 ) : E r2 = 0 . !42 '7 i nWa l l - t h i ckness pe r UG-15(b ) : t r 3 = 0 .0525 i nS td p ipe na1 l pe r Uc -as (b ) (a ) : E r4 = 0 .28175 inThe greater of t r2 or t r3: t r5 = 0 - !427 LnThe lesser of tr4 or tr5: tr6 = 0 - L427 in
Req'd per t tG-45 is the larger of ! r1 or t r5 = o-L427 ln
-Available /rozzl-e wa11 thickness new. tn = 0 .25 in
The nozzfe neck thickness is adequaEe for MAWP.
AlLowab1e stresses in joints lrc;-45 (c) and III|-15 (c)
croove weld in tension = o.74*1"6700 = 1-2358 psiNozz le wa l l i n shea r = 0 .7 *15700 = 11690 ps iInne r f i l l e t we ld i n shear = 0 .49*15700 = 8L83 ps i
Strenqth of welded joints:
R.EVOv049-1-073P,.ge23 of29
3 . L 2 - L 9 9 6
N2-RIGHT
(1) lnner f i l let weld in shear( P i / 2 ) * N o z z l e O . D . * L e g * S i = 1 . 5 7 * 8 * 0 . 2 5 * 8 1 8 3 = 2 5 6 9 4 . 5 2 l b f
(3) Nozzl-e wal l in shear( P i / 2 1 * 1 ' , 1 g t t n o z z l e d i a . * t n * S n = ! . 5 7 * 7 . 7 5 * 0 . 2 5 * 1 1 5 9 0 = 3 5 5 5 9 . 5 2 l b f
(4) Groove weld in tension( P i l 2 ) * N o z z ] e O . D . * t w * S g = 1 . 5 7 * 8 * 0 . 1 8 7 5 * 1 2 3 5 8 = 2 9 1 0 3 . 0 9 l b f
Loadino on velds oer UG-41 (b) (1)
W = (a - (d - 2 * tn ) * (81* t - F * t r ) ) *Sv= ( 1 . 1 0 8 9 - ( 7 . 7 7 I - 2 * O . 2 5 1 * ( 1 * 0 . 2 5 - t * O . L 4 2 ' 7 ) ) * 1 6 7 0 0= 5489 -6s2 l -bf
W1-1 = (A2 + A5 + A41 + A42) *go'= ( 0 . 2 9 + 0 + 0 . 0 5 3 + 0 ) * 1 5 7 0 0= 5 8 9 5 . 1 l b f
W2-2 = (A2 + A3 + A4L + A43 + 2*tn*t* fr1) *Sw= ( 0 . 2 9 + 0 + 0 . 0 5 3 + 0 + 2 * 0 . 2 5 * 0 . 2 5 * l ) * 1 5 7 0 0= '1982.5 lbf
Load for path l - -1 Lesser of v l or W1-1 = 5489.652 lbfPa th 1 -1 Th ru (1 ) & (3 ) = 25694-62 + 35559 .52 = 6 t254 .14 l b fPath 1-1 is stronger uhan w so i t is acceptable per UG-41(b) (2)
Load fo r pa th 2 -2 l esse r o f W o r w2-2 = 5489 .652 l b fPaL} : 2 -2 th ru (1 ) , (+ ) = 25694 .62 + 29103 .09 = 54797 .71 - l b fPatsh 2-2 is stronger tshan w so i t is acceptable per UG-41(b) (2)
Reinforcement Calculations For Nozz1e MAP
Limits of reinforceEEnt tE-4O
Paral le l to the vessel wal l d = 7.77L inNormal to the vessel wal l outside 2.5* ( tn-Cn) + te = .525 inNorma1 to the vessel wal l inside 2.5* 1tn-Cn-C) = .525 in
Deter0inat ion of Chord Length
Ttretal = ArcCos ( (Lo + Rn) /Rm)= A rcCos ( (15 .75 + 3 .75 ) / 60 .32L35)= 7L .L3958
TheLa2 = ArcCos ( (f,o - Rn) /Rm)= a , r ccos ( (15 .75 - 3 .75 ) / 60 .32L35)= 7 8 . 5 2 s 7 6
d = 2 *Rm*S in ( (The ta2 - The ra l ) / 2 )= 2 *6Q.321"35*S in ( (78 - s2575 - ' 7 t . t 3958 ) /2 )= 7 . 7 7 L i n
REVOv049-r-073Page U of 29
3 . L 2 . L 9 9 6
N2-RTGHT
^ Nozzle required thicl,oess-
E r n = P * R n / ( S n * E - 0 . 5 * P )= 79 .06141*3 .75 / {15700*1 - 0 .6 *79 .O674L)= 0 .01 -78 i -n
Required thiclqress tr frdtr ltc-37 {a) (1)
t r = P * L * M / ( 2 * S * E - 0 . 2 * P )= 7 9 . O 6 a 4 a * 5 0 . 2 5 * 7 / ( 2 * 1 5 7 0 0 * L - 0 . 2 * 7 9 . 0 6 t 4 1 )= 0 . 1427 i n
Area reouired
A1lowab1e stresses: Sn = t-5700, Sv =
f r1 = l esse r o f 1o r Sn /Sv so f r1 =1f r2 = l esse r o f 1o r Sn /Sv so f r2 -1
A = d * t r *F + 2 * tn * t r *F* (L - f r 1 )= 7 . 7 7 ! * 0 . ! 4 2 7 * 1 _ + 2 * 0 . 2 5 * 0 . ] - 4 2 7 * ! * ( L= 1 . 1 0 8 9 i n ^ 2
Area available
A1 = larger of Uhe following
1 -6?00 , ps i
= .834 in^2
- 1 )
= d* (E1* t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 7 . 7 7 L * ( 1 r . 0 . 2 5 - 1 * 0 - ! 4 2 7 ) - 2 * O - 2 5 * ( 1 * 0 . 2 5 - 1 r . 0 . ! 4 2 7 ) * ( L - I \= . 8 3 4 i n ^ 2
= 2 * ( t+ tn ) * (E1* t -F * t r ) - 2 * t . n * (E l_ * t -F * t r ) * (1 - f r1 )= 2 * 1 0 . 2 5 + 0 . 2 5 ) * ( 1 * 0 . 2 5 - 1 * O . L 4 2 7 | - 2 * O . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . L 4 2 7 1 * ( ] - - ] - � )= . lO7 i rL^z
A2 = smal ler of the fol lowinq = O.29 in^2
= 5* ( tn - t rn) * f r2*E= 5 * ( 0 . 2 5 - 0 . 0 1 7 8 ) * 1 * 0 . 2 5= .29 i r .^2
= 5 * ( t n - t r n ) * f r2 * tn= 5 * ( 0 . 2 5 - O . 0 1 7 8 ) * 1 * 0 . 2 5= .29 in^ 2
A41 = Leg^2*fr2= 0 . 2 5 ^ 2 * ! = . 0 6 3 i n ^ 2
A r e a = / { 1 + A 2 + A 4 1= 0 . 8 3 4 + 0 . 2 9 + 0 - 0 5 3= 1 . 1 8 7 i n ^ 2
As Area > A the reinforcement is adequate for MAP = 79.06141 aE 70 Deg
REVOv049-1473PaEe2S of29
3 . L 2 . L 9 9 5
N2-RIGET
Reinforcement check in the p].ane parallel to the 1ong. axis
Area required
A = d * t r *F + 2 * tn * t r *F* (1 - f r l )= 7 . 5 * 0 - 1 4 2 7 * ! + 2 * 0 . 2 5 * 0 . L 4 2 7 * ! * ( 1 _ 1 )= 1 . 0 7 0 2 5 i n ^ 2
Area awailable
A1 = larger of the fol lowing = .805 in^2
= d * (E1* t_F* t r ) _ 2 * tn * (E l * t . _F* t r ) * (1_ f r1 )= 7 , 5 * ( 1 * 0 , 2 5 - 1 * 0 . 1 4 2 7 ) - 2 * 0 . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . 1 4 2 7 ) * ( L - 1 )= . 8 0 5 i n ^ 2
= 2 * ( t+ tn ) * (E1* t -F * t r ) - 2 * !n * (E1* t -F * t r ) * (1 - f r1 )= 2 i ( ( 0 - 2 5 + O - 2 5 ) * ( 1 * 0 . 2 5 - 1 * 0 . 1 4 2 7 ) - 2 * 0 . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . ! 4 2 7 ) t ( ( L - a )= . l - 07 i n^2
A r e a = A 1 + A 2 + A 4 1= 0 . 8 0 5 + 0 . 2 9 + 0 . 0 5 3= l - . 1 5 8 i n ^ 2
As Area > A the reinforcement is adequate for MAP = 79.06141 at 70 Deg F
t Check the welds - From IIW-15(d):
tmin = Lesser of 0.75 0r tn or t , , tsmin = 0.25 int1 o r t2 (min) = lesser o f 0 .25 or o .7* tmin , t1 (min) = 0 .L75 int 1 ( a c t u a l ) = 0 . 7 * L e g = 0 . 7 * 0 . 2 5 = 0 . 1 7 5 i nts2 (ac tua l ) = 0 .1875 int .1 + t2 = 0 .3625 >= 1 .25* tn r in
The we]-d sizes for t.1 and t2 are satisfactory.
IIG-45 Nozzle Neck Ttrickness Check
Wal-l t .hickness per UG-45 (a) : tsr1 = 0 .0178 in (E = 1)wa1I t ,hickness per UG-45 (b) (1) : tr2 = 0 .L427 inWal1 thickness per UG-16 (b) : tr3 = 0.0625 inStd pipe vral l per UG-45 (b) (a) : tr4 = 0 .281-75 inThe greater of tr2 or tr3: tr5 = 0 -L427 j .rLThe lesser of tr4 or trs: tr5 = 0 . L427 ln
Reqtd per UG-45 is the larger of tr1 or tr6 = 0.1427 in
Available nozzl-e wa11 thickness new. tn = 0.25 in
The nozzle neck thickness is adequate for MAP.
A]-lowalo].e stresses in joints IIG-45 (c) and Utf-15{c)
REVOv049-1473Pago 26 of29
3 -L2 .L995
N2-RIGET
Groove weld in tension = O.74t !6700 = 12358 psiNozz le wa l1 i n shear = 0 .7 *L670O = L1690 ps iInner f i l let r rreld in shear = 0 .49*l-5700 = 8183 psi
Strenqth of welded ioints:
(1) Inner f il"Let weld in shear( P i / 2 ) * N o z z l e O , D . * t e g * S i = 1 . 5 7 * 8 * 0 . 2 5 * 8 1 - 8 3 = 2 5 6 9 4 . 5 2 l b f
(3) Nozzle wal l in shear( P i l 2 ) * M e a n n o z z l e d i a . * t n * S n = L . 5 7 * 7 . 7 5 * 0 . 2 5 * L l - 5 9 0 = 3 5 5 5 9 . 5 2 l b f
(4) Groove weld in tension( P i / 2 ) * N o z z l e O . D . * t w * S g = 1 . 5 7 * 8 * 0 . 1 8 7 5 * 1 2 3 5 8 = 2 9 f O 3 . 0 9 l b f
Loadina on welds Der IIG-41 (b) {1)
W = (a - (d - 2 * t . n ) * (81* t - F * t r ) ) *Sv= ( 1 . L 0 8 9 - ( 1 . 7 7 \ - 2 * O . 2 5 ) * ( 1 * 0 . 2 5 - ! * O . ! 4 2 7 ) \ * ! 5 7 0 0= 5489 .652 l -b f
W1-1 = (A2 + A5 + A4l- + A42) *g\ t= ( 0 . 2 9 + 0 + 0 . 0 6 3 + 0 ) * 1 5 7 0 0= 5 8 9 5 . 1 l b f
W2-2 = (A2 + A3 + A41 + A43 + 2*!n*t* fr1) *Sv= ( 0 . 2 9 + 0 + 0 . 0 5 3 + 0 + 2 * 0 . 2 5 * 0 . 2 5 * A ) * 1 6 7 0 0= 7982 .6 ]b f
Load fo r pa th 1 -1 l esse r o f W o r W l - - l - = 5489 .552 l b fPa th 1 -1 th . ru (1 ) c (3 ) = 25694-62 + 35559 .52 = 6L2s4 .14 Lb fPath L-1 is stronger than w so i t is acceptable per UG-41 (b) (2).
Load for paEh 2-2 lesser of w or vI2-2 = 5489.652 1bfPaEh 2 -2 th r r (1 ) , (4 ) = 25694 .62 + 291 -03 .09 = 54797 . ' 1L Lb fPaE}l 2-2 is stronger than w so i t is acceptable per UG-41-(b) (2).
Reinforcement Calculatioas for brEerna]- Pressure
Limits of reinforcement UG-40
Para1le1 to the wessel waI1 d = 7,77 lnNormal tso lhe vessel wal- l outside 2.5* ( tsn-Cn) + te = .625 inNormal to the vesseL waI1 inside 2.5* ( tn-Cn-C) = .625 in
Deternination of Chord Lenglth
Thelal_ = Arccos ( (i.,o + Rn) /Rm)= A r c C o s ( ( 1 5 . 7 5 + 3 . 7 5 ) / 5 0 . 3 4 5 8 5 )= 7 ] - . 14795
Ther,a2 = Arccos ( (r,o - RrI) /Rm)= A r c c o s ( ( 1 5 . 7 5 - 3 . 7 5 ) , / 5 0 . 3 4 6 8 5 )
REVOv049-l-0?3Pagez? oI29
3 .L2 -L996
I
}I2 -RIEET
= 7 8 . s 3 0 6 9
d = z *Rm*s in ( (TheEa2 - The ta l ) / 2 )= 2 * 6 0 . 3 4 5 8 5 * S i n ( ( 7 8 . 5 3 0 5 9 - 7 1 - . 1 4 7 9 5 ) / 2 )= 7 . 7 7 i n
Nozzle resuired thiclmess
L / D o = 5 . 0 e 2 / e = . 6 3 5 2 D o , / r , = 8 / O . O 2 2 0 5 = 3 5 2 . 8 1 1 8From t ,ab le G : A = 0 .000317From tab le HA-3 : B = 4L94 .4
Pa= 4*B/ ( 3 *Do/t )= 4 * 4 L 9 4 . 4 / ( 3 * 8 / O . 0 2 2 0 5 )= L5 .4 i . 44 ps i
Nozzle required thickness Ern = .02205 in
Reauired thickness tr frm IE-37(d) (1) = .1937 in
Area recruired
Al lowable stresses: Sn = L4700, Sv = t-4700, psi
f r1 = l esse r o f 1o r Sn /Sv so f r1 =1fr2 = Iesser of 1 or Sn/Sv so fr2 =1
A = 0 . 5 * ( d * t r * F + 2 * t n * t r * F * ( 1 - f r 1 ) )= 0 . 5 * ( 7 . 7 7 * 0 . L 9 3 7 * L + 2 * 0 . 2 5 * 0 . 1 9 3 7 * 1 * ( 1 - 1 ) )= .7525 !rL^2
Area avai1able
41 = larger of tshe following = .437 !t^2
= d * (E1* t -F * t r ) - 2 * tn t r (E l * t -F * t s r ) * (1 - f r ] . )= 7 . 7 ' 7 * ( 1 * 0 . 2 5 - L * 0 . 1 9 3 7 ) - 2 * O . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . 1 9 3 7 ) * ( 1 - 1 )= .437 ir.^Z
= 2 * ( t+ tn ) * (E1* t s -F* t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 2 5 + 0 . 2 5 ) * ( 1 * 0 . 2 5 - 1 * 0 . 1 9 3 ? ) - 2 * 0 . 2 5 * ( 1 * 0 . 2 5 - 1 * 0 . 1 9 3 7 ) * ( 1 - 1 )= . 0 5 6 i n ^ Z
A2 = smal ler of the fol lowinq = 0.285 in^2
- t r * I f n - i ? n l * f r- , - - , - - 2 * E= 5 * ( 0 . 2 5 - O . 0 2 2 0 5 ) * 1 * 0 . 2 5= . 2 8 5 i n ^ 2
= 5 * ( t . n - ! r n ) * f r2 * tn= 5 * ( 0 . 2 5 - 0 . 0 2 2 0 5 ) * 1 * 0 . 2 5= -2 t35 t l 2
REVOv(x9-t4?3Page 28 ofzg
3 . L 2 . L 9 9 6
N2_RIGEI
A4L = Leg^2* fr2= Q .25^2*1 " = .063 i n^2
A r e a = A 1 + A 2 + A 4 L= 0 . 4 3 7 + 0 . 2 8 5 + 0 . 0 6 3= . 7 8 5 i n ^ 2
As Area > A the reinforcemenL. is adequate for Pe = t-5.3L362 at 400 Deg F
Reinforcement check in the pl-ane para]-le]- to the longi - axis
Area required
A = 0 . 5 * ( d * E r * F + 2 * t n * t r * F * ( l _ _ f r 1 ) )= 0 . 5 * ( 7 . 5 * 0 . 1 9 3 7 * 1 + 2 * 0 . 2 5 * Q . L 9 3 7 * L * ( 1 - 1 ) )= .725375 !n^2
Area available
4L = Larger of the following = -422 j -n^ 2
= d * (E1* t -F * t r ) - 2 * tn * (E l * t -F * t r ) * (1 - f r1 )= 7 . 5 * ( 1 * 0 . 2 5 - 1 * 0 , 1 9 3 1 ) - 2 * 0 . 2 5 * ( 1 - * 0 . 2 5 - 1 * 0 . 1 9 3 7 ) * ( 1 - 1 )= .422 j-r:^2
= 2 * ( t+ tn ) * (E1* t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 2 5 + 0 . 2 5 ) * ( 1 * 0 . 2 5 _ 1 * 0 . 1 9 3 7 ) _ 2 * 0 - 2 5 1 ( 1 * 0 . 2 5 _ t - * 0 . 1 9 3 7 ) * ( 1 - 1 )= . 0 5 5 i n ^ 2
A r e a = A 1 _ + A 2 + A 4 1= 0 . 4 2 2 + 0 . 2 8 5 + 0 . 0 6 3= .77 i -n^2
As .A.rea > A the reinforcement. is adequate for Pe - 15.3a362 aL 400 Deg F
UG-45 Nozzle Neck Tlxickness Check
wall t,hickness per UG-45 (a) :wall thickness per UG-45 (b) (2) :walL tshickness per UG-16 (b) :Std pipe wal1 per UG-4s (b) (4) :The great.er of Er2 or tr3:T'he lesser of tr4 or tr5:
= 0 . 0 2 2 0 5 i n ( E = 1 )= 0 . 0 3 1 4 i n= 0 . 0 6 2 s i n= 0 . 2 8 1 7 5 i n= 0 . 0 6 2 5 i n= 0 .0625 i . n
t r 6 = 0 . 0 5 2 5 i n
= 0 . 2 5 i n
trl-ET2t,13Er4t15tr5
Req'd per UG-45 is the l-arger of tr1 or
Avail-able r:ozzLe wall- t.hickness new, tn
The nozzle neck thickness is adequat,e for Pe.
REVOv049-l_0?3Page 29 of29
3 . t 2 . L 9 9 6
ENGINEERINGCALCULATIONS
No:Voqq_/- dzPAGE I OFF
f-.O--rcAOl Nd eetr= Des i 6r.J
EB9,JEeI: Lr Go PROJECTNO: V.fgo49
I\IETHOD: .SoHpe-ESs sls.-3 CoP,lJrE< pAEssrji€ vssse.,- SoEi:w6A€
REFERENCES: _.--O-eE. No.r.,\/o4_i - f.rr- -r3P\,G' r io-_ Vo49-4 -c)4>
D o e . - . N o , / a y { - i - D a 6 , z / t , a l ? , < ; * a . F E ' s t ' , , ! ' o ' t r - a ' 1 n ' 1 *
CAIfULATIONS: (SEE ATTACIIED)
iGO ,s i^J CoaL-cA;FlANcE- wtTFl;_REQureraueNrt
Doc No. V4S1474
Prle I of 38
TESLE- oc Co,JlEurs
t . - 3copg:Z. - DE-grc.KJ CP-ri-r,-r { I3. .. HoDE(-4, - CoF4FR/=SS \s.-t3 - InrP,or- DA]-a\t - CoHP{EsS \s. s-3 - 6g;teui-
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4
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REVODoc No, V49-1474Pae€ 2 of3E
GuAurpY -Ir€-
€14" Hnpt C.:va< -n ASPTE @
Raq,r^r LErler-il> Fo!-1+e- Na+-.zq: L,{your .a,sPs I ^ra CusmPel- Ar'EPT-AN'E Yea-Doc. No . vo41 - pL- ,/o
Z Dr=sreo CAtr-€tat A:
€xr. . t4." ASI-I- =. ,fOOoF
- [ r [oa=ua Loa4r,oNr Drnq:
Nt C , = 1 .87€ " , ' 6 , = o '/
Nz- r-- = yffiffit - zz.Gu't ' 6'o-Fa*-'a€.urr.G1.7.
N 3 G = f z ' L 2 . 6 6 " ) 4 - O o - a q , 1 \ + 7 t ? o z z s o . o "
N+
Ns-
%- /rO.Ar:S.+zo.srz\ '1 - 23,61" / ' A =-i ir l - '
f f i = 8A3"
(3 : Ia' . zs.6 | " : () - (1O - 26.00)i Z?4, a -3\: I, lF,a-/
REVO
Doc No. V49n{74
Prse 3 ot 38
€3r,97.
c o o
I
4 - CorrPrQes> ..'.s$ - lNpor D4r.iSj-
F tD Heao ', sA
No?eLgS (,cee\
Lo*"-. Sr=,qr X.RaY- gEatir,Ess ." Nr6 XRAY
ltsao/S*Eu\ SEAI-I X- Rar- SDor DE4- U|w - t l (b \ BP,= t
ro = 84.e-f n
CRorrunt lr*rrEArvar-T,ru rr.lS = €€'
(Auu\
DrsTA\)c.E- r
n : 7 . 8 F '
t u o 2 2 , 6 L a
G ' z z , t r - '
C 1 - z s . o t '
16 e - l 3 .O I "
- A*a.-e- @
N,['. 6,= o'
N\2: A? z Gi .1o
\E l3 : A3 -2Q6 , ' 7 '
Nc i 6a - Z1 .O jo
Nl<' . 6sz-331,?70
?4,6 G64L # '6F i
sA46 064 L H,GFI
= 1 4 . ? R S ,
o o o6 0 0
3{ f.t c{
bgsreu -T-EtqF. = 4doqF
. Kr,rUCnLE ln,t=p.na*RqsruS =.t2-f "
. FOp'HTNG Auuor^rr<Uc€. :-6'
. Sraar c,r+r f-t-nu@,g- = Za
. l [ 1 q - g N , = . q q = . 3 r 5 ^
ID = ?.75" (A-. )
-T-t+rcxt.r rg:Ss = . l8?s-
REVODoc No, V4ll-074P|s. 4 of38
o ? z L A S i
0 0 0
6olpur Fop- 84. F+D l{e.ao, tr{ozzce> l,zAuO < Ap-e- ,{rrncr+EA li Vpr.reY CospuAUc€-I*o
ASr^aC_Wf. . €or?or.J, /^:CLr-rDlruc.A C AOOepoa,
f{ora' -TFor,(uauvsrs
/R.esr-r: Fo a- Na>Zutza\3 l-s svrqr4gr*-rc,aLLY tDE.utte.ae TZ>
T. t * tozz+ la bL .Aub Nozzca€€- tsloeur1 c,(a -rb n 4.
REVODoc No. v49r-074Prcc 5 of3E
.i .i .{
/r?.\(69 )\J/
o
TABLE OF COIfIE$TS
Pressure SurmnaryWeights SumrnaryNozzle Surmarv
1
5
o
152 4
3 Z
Thickness Summary84N F&D HAM HEADN1-1ST ROW. CENTERN2-1ST ROW-RTGHTN4_2ND ROW-RIGIIT
Total Pages In This Report
REVODoc No. V49-r-074Psft 6 of 18
3 . L 2 . L 9 9 6
Pressure Sumarv
Pressure sumary for oressure chmber 1
l N o E ! ] e I r I n A x P I l t r a F
i status I des. tgr | |
| ( u c - - 4 5 ) | ( d s E F ) | l p s l ) I { p 6 i )
I E€ | uc-ee I Ecs-66 lcol loaior I
l e r i € r n l r l R a t l o I x D u T E r e b p E i o ! o r l } l l o r a n c e l
| { p 6 i ) | | (des P i s r r .66 Reduct jo ! i ( rn ) I
t - l
I o . o o o I
I o . o o o I
I o . o o o I
I o . o o o I
| 0 . 0 0 0 I
| 0 . 0 0 0 |
t - t _ l _ t _ l _ lo - o I t 2 - r | 7 z - a | 2 2 . { l 1 . o o o I
o . o I s 3 . s I s 3 . s | I s . ? I 1 . o o o I
o . o I 8 3 . 2 | 8 3 . o I 1 5 . B l 1 . o o o I
0 . 0 I 8 3 . 2 | 8 3 . 0 | 1 5 . 6 | 1 . 0 0 0 |
o . o I s 3 . 2 | 8 3 . o | 1 5 . 8 | 1 . o o o I
o - o I 0 3 . 2 | s 3 . o I l s . B | 1 . o o o I
| 8a' FeD EAx EraD I
I r l {1-lsr Ror-cEl{TB I
I rs2 r{2-1sr Ror-RrcET I
I s3 tr3-lsr Rora-lBrr I
I rr4 x4-2{D ROr-RIGET II ts ras-2xD Ror-laar I
I r [oa rpp ! !c .b le
l r [ o E . p p ] i c r b l e
l r o r . p p l i c . b l e
I ro l lpp l i cab le
I ro r app l i cEb le
l l a o t l p p l i c a b l e
I
Vessel MAWP hot & corroded is 72.11 psi @ 0 degrees F.
Vessel MAP new & col"d is 72 -Ll psi @ 70 degrees F.
Vessel al lowable external pressure is 15.75 psi @ 400 degrees F.
Hydrotest. pressure ca].culation based on llAltp
= 1.5* (MAWp + Operating Liquid Head)*1 = 108.2 psi
vessel hydrotest pressure is 108.2 psi.
Note: vessel UAP ratinq not v-alid udess hldrotest pressure based on UAP-
REVODoc No. V491-0t4P.pe 7.f34
3 -L2 -L996
c o r D o r o l t - - - - - - ^ - t e i g h t ( 1 b s )
le ta t l !€ la l , r ra9s Pacx€aI
co ! ! e BUD Beata
weiqht SuEEarv
co l t l lbu t€d by veE.e l E le&e!E.
IDsr l L iD iEg ? iP ing r radder RlaE! oDe! TcEt t toz r le
r { i sc l rqu id L iqu id & l lE& p t r t
8 { i l E d b r ! h e a
4 1 4 9
verae l ope la t iDg De igh t . co t roded: a5o lbs
vesae] e rPBy r€ ig l t ! , cor ro i te r t : 850 lbE
vesae l eupty re igh t , !e . : 350 lbE
v e s a E l t € E l e € l g b l , D e r : 2 , 9 9 9 l b 6
vessel center of qralrity location (frm right weld seam)
vessel l- i f t weight, new:Center of gravity to seam:
848 lbs1 0 . 6 i n
REVODoc No, Va9-t-074P.e€ E of 38
3 -L2.L996
Nozzle Sumary
OD
( i t r ) { i D } ( t . )( i D ) A 1 ? A 2 ? { i ! } ( l )
N I
N2
lir3
N4
a . 0 0 0 . 2 s 0 0
a - 0 o 0 . 2 5 0 0
a . 0 0 0 . 2 5 0 0
a . o o 0 . 2 5 0 0
0 , 3 ? 5 0 0 . 2 7 7 7
o , 3 7 5 0 0 . 2 7 8 9
0 . 3 7 5 0 0 . 2 ? 8 8
0 . 3 7 5 0 0 . z 7 B f
0 . 3 ? 5 0 0 , 2 7 9 0
0 . 0 0 0 0 1 0 0 . 1
0 . 0 0 4 0 1 0 0 . 0
0 . 0 0 0 0 1 0 0 . 0
v
v
v
v
v
v
nozzle thickness- rrozzLe thickness required per UG-45/15
vessel wall thicknessrequired vessel watl thickness due to pressure + corr per uG-37
- local wessel wall thickness (near opening)area available per UG-37, gowerning conditionarea required per UG-3?, governing conditioncorrosion allowance on nozzle id.
0 . 2 1 0 s
0 , 2 1 0 1
0 . 2 1 0 1
o . 2 1 0 1
0 . 2 1 0 1
0 - 3 7 5 0
0 . 3 ? 5 0
0 . 3 7 5 0
0 . 3 7 5 0
o - ! ? 5 0
t n -Req tnN o m t -R e q t -User t
A r -Corr -
REVODoc No. V49-l-{}74Pme 9 of36
3 - 1 2 . 1 9 9 6
lllicloess srmarv
coDpo leDr ID Lengrb ! {o r0 c R€q r Jo ln t Gove-n iDg Det loc t
r i l e D r i f i c ! ( i n ) { i ! ) { l D l { t D ) E r o . d s r a r u E s E r e . r ( i n )
g r t r l & d h r 6 b e a d a a . 2 s 0 - 3 7 5 0 0 . 3 ? 5 0 0 - a s
Nom t - vessel wal-I thicknessReq t - required vessel- walL thickness due to gioverning loadingE - longitudinal seam joint efficiency
Load:internal - circ stress due Eo int.ernal pressure governsext.ernal- - external Dressure qovernswind - combined
-Long strel" due to sTATUs + wind govertls
seismic - combined long stress due !o STATUS + seismj.c governs
REVO
Doc No. V49-1474
P,ce l0 of383 . L 2 . L 9 9 5
84N FED HAM IIEN)
ASUE Section VIII Division 1. 1992 Edition. A93 .Addenda
Corrosion allowance: Inner C = 0 Outer= 0
P$llff is not performed
Radiography: Category A joints - Seamless NO X-RayHead to she1I seam - Spot UW-11(b) type
qomponent:Material specif ication :
Estimated weight :capacl_ty :
ID = 84.25 crolvn 1. , =
Straight flange = 2
F&D headSA 240 3O4L HTGH
new = 821 .5 co r r = 82L .5f l ew = 257 .55 co r r = 257 .65
84 .25 knuck le r = 5 .25 L
forming allowance = 0
-LDUS
in (min)
ga
an
tJfAp: (New & at 70 deg F) Appendix 1-4 (d) E(I 3
P = 2 * S * E * t / ( L * M + 0 . 2 r t ) - p s= 2 * 1 5 7 0 0 * 0 . I 5 * 0 . 3 7 5 / ( 8 4 . 2 5 * ! . 7 5 1 5 + 0 . 2 * 0 . 3 7 5 ) -= 7 2 . 1 1 0 0 8 p s i
I rrrAnP: (Corroded & ar O deq F) Appendix 1-4(dl Eg 3
P = 2*S*E* ts / (L* t \ , l + 0 .2* t ) - Ps= 2 * 1 5 7 0 0 * 0 . 8 5 * 0 . 3 7 5 l ( 8 4 . 2 5 * 1 . 7 5 1 - 5 + O . 2 * 0 . 3 7 5 ) -= 7 2 . 1 1 0 0 8 D s i
Maximrm A.Llowab]-e Externa]- Pressure: (Corroded @ 4OO degr F)
A = .a25/ (P .o / t )= - a 2 s / ( 8 4 . 6 2 s / 0 . 3 7 5 \= U . U U U 5 f , 4 t
From table I IA-3: B - 5065.4
Pa= B / (Ro / r )= 5 0 6 s . 4 / ( 8 4 . 6 2 s / 0 . 3 7 s )= 22 .4454 ps l
Check the Maximum External Pressure: Uc-33 (a) (1) & App. 1-4(d)
p e = 2 * S * E * t / ( ( M * t o - g * ( M - 0 . 2 ) ) * L . 6 7 )= 2 * ! 4 7 O O * ! * O . 3 7 5 / ( ( 1 . 7 s l s * 8 4 . 6 2 5 - 0 . 3 7 5 * ( 1 . 7 5 1 5 - 0 . 2 ) ) * L , 5 7 )= 4 4 . 7 1 5 8 4 p s i
Ttre maxirmrm allowable external pressure is 22.4454 psi.
REVO
Doc No- V49-l'{n4
P:re lr ol383 -L2 -L996
l[1-1sT RoW-eStTER
Opeoiinq N1 Reinforcement Calculations Per lre-37
Located on: 84' F&D I{AM HEADUser input vessel thickness: .375 inLiguid stat ic head included: 0 psiFl-ange description: Not instaLled
Nozzle material specif icat ion: SA 240 304L II IGII
Nozzle orientat,ion: 0 degreesEnd of nozzle to datum line: ]-9.782 inNozzLe calculated as hi l- lside: vesPro jec t ion ou ts ide vesse l Lpr : i . :g in
En ->
twl"->< - d - >
v
c o r r o s i o n a l l o v r = 0 i nnoz thick new cn= .25 innozz\e id. new d= 7.5 inf i1l-et weld tw1 = .25 ingiroove weld tw2 = .1,875 in
To head cenler R= 7.875 i .n< - R
-l-*,I- > l
I Reinforcement Calculations For Nozzle It{AwP
Li riLs of reinforcenent lrci-4o
Paral lel to the wessel wall d = 7.533 inNormal to Ehe vessel wall outside 2.5* (tn-Cn) + te = .525 inNormal to the vessel wall inside 2.5* (tn-Cn-C) = .525 in
Detemination of ehord Lengrth
Ttretal = ArcCos ( (I-,o + Rn) /Rm)= Arccos ( (7 .87s + 3 -75) /84 .3554)= 6 Z . U I > 5 2
Theta2 = Arccos((L,o - RrI) /RIn)= A r c c o s ( ( 7 . 8 7 5 - 3 . 7 5 ) / 8 4 - 3 5 5 4 )= 6 t . L t t l d
d = 2*Rm*Sin( (Ttreta2 - thetal) /2)= 2 * 8 4 . 3 5 5 4 * S i n ( ( 8 7 . t 9 7 5 8 - 8 2 . 0 7 9 3 2 ) / 2 )= 7 . 5 3 3 i n
Nozzle required thiclsress
t rn = P*Rn / (Sn*E - 0 .6 *P)= 8 3 . 5 3 0 5 7 * 3 . 7 5 / ( ] - 6 7 0 0 * 1 - 0 . 5 * 8 3 . 5 3 0 5 7 )= 0 . 0188 i n
REVO
Das N!. v4q 1-074
Paoe l2 of363 .L2 .L996
N1-1ST RO9|-CH[-TR
Required thickness tr frm lre-37(a) (1)
t r= P*L*M/ (2 *S*E - 0 .2 *P)= 8 3 . 5 3 0 5 ? * 8 4 . 2 5 * A / ( 2 * 1 6 2 0 0 * 1 - 0 . 2 * 8 3 . 5 3 0 5 7 )= 0 . 2 1 0 8 i n
Area reguired
Al lowable stresses: Sn = L67OO, Sv = l -6700, psi
f r1 = l esse r o f 1o r sn /Sv so f r1 =1f r2 = l esse r o f 1o r Sn /Sv so f rZ =1
A = d * t r *F + 2 * tn *L r *F* (1 - f r 1 )= ? . 5 3 3 * 0 . 2 1 0 9 * 1 + 2 * 0 . 2 5 * 0 . 2 1 0 8 * j _ * ( 1 - 1 )= 1 . 5 8 8 i n ^ 2
Area avai]-able
A1 = larger of the following = a.237 Lrj.^ 2
= d * (E1* t s -F* t r ) - 2 * tn * {E1* t -F * t r ) * (1 - f r1 )= 7 . 5 3 3 * ( 1 : t 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) * ( 1 - 1 )= L . 2 3 ' I i n ^ 2
= 2 * ( t + t n ) * ( E 1 * t - F * C r ) - 2 * t n * ( E 1 * t . - F * t r ) * ( 1 - f r 1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) * ( 1 - 1 )= .205 i n^2
A2 = smal1er of the fol lowing = 0.289 in^2
= 5 * ( t sn - t r n ) t f t 2 *E= 5 * ( 0 . 2 5 - 0 . 0 1 8 8 ) * 1 * 6 . 3 7 5= .433 i n^2
= 5 * ( t n - t r n ) * f r2 * tn= 5 * ( 0 , 2 5 - 0 . 0 1 8 8 ) * 1 * 9 . 2 5= .289 i r '^2
A4! = Leg^ 2* frz= 0 . 2 5 ^ 2 * L = . 0 5 3 i n ^ 2
A r e a = A 1 + 4 2 + A 4 1= L . 2 3 7 + 0 . 2 8 9 + 0 . 0 5 3= l - . 589 i n^2
As Area > A the reinforcement is adequatse for MAWP = 83.53057 at o Deg F
Reinforcement check in the plane parallel to tshe lsnq - axis
Area required
I t A = f l*91*p + 2*tn*tsr*F* (1 - fr1)REVO
Doc No. Va9.l.0?4
P.sc l3 of383 .12 . 1995
lfl-1sT ROI{-CMTTBR
= 7 . 5 * 0 . 2 1 0 8 * 1 + 2 * 0 . 2 5 * 0 . 2 1 0 I * 1 * ( 1 _ 1 )= 1 . 5 8 1 i n ^ 2
Area avai].able
AL = l-arger of the following = 7.23r i'a^ 2
= d * (E1* t s -F* t r ) - 2 * !n * (E1* t -F * t r ) * (1 - f r1 )= 7 . 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 - 0 8 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 L 0 8 ) * ( 1 - 1 )= 7- .231- in^ 2
= 2 * ( t+ tn ) * (81* t -F * t r ) - 2 * tn * (E1* t -F *Cr ) * (1 - f r1 )= 2 * ( 0 . 3 ? 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) * ( 1 - 1 )= . 2 O S ! n ' 2
A r e a = A 1 + A 2 + A 4 1= ! . 2 3 r + 0 . 2 8 9 + 0 . 0 6 3= 1 . 5 8 3 i n ^ 2
As Area > A the reinforcement is adequate for MAWP = 83.53057 at 0 Deg F
Check the Ye]-ds - Frqn Uw-16 (d) :
tm in = Iesse r o f 0 .75 o r t n o r t , tm in = 0 .25 i nt1 o r t 2 (m in ) = l esse r o f 0 .25 o r o ,7 * tm in , t 1 (m in ) = 0 .175 i nt 1 ( a c t u a l ) = 0 . 7 * L e g = 0 . 7 * 0 . 2 5 = A . 1 7 5 i nt 2 ( a c t u a f ) = 0 . 1 8 7 5 i nt1 + t .2 = O .3525 >= l - .25*tmi.n
The weld sizes for t1 and t2 are sat isfactory.
IIG-45 Nozzle Neck lbickness Check
Wal l th ickness per I IG-45 (a): t r l - = 0.0188 in (E = L)Wa1 l t h i ckness pe r Uc -as (b ) (1 ) : L r2 = 0 .2108 i n91a11 th i ckness pe r UG-16(b ) : t r 3 = 0 .0525 i nSt.d pipe wal l per UG-as (b) (a) : t r4 = 0 ,28L75 inT'lre greatser of tsr2 or tr3 : tr5 = 0 .2108 inTlre l -esser of t r4 or t r5: t r5 = 0.2108 in
Req'd per UG-45 is the larger of t r1 or t r5 = 0.2108
Available ]j.ozz]-e waII thickness new, tn = 0.25 in
The nozzl-e neck thickness is adequale for MAWP.
Allowable stresses in joints ucl-45 (c) and ltw-15 (c)
Groove weld in tension = 0.74*1-5700 = 12358 psiNozzle wal l in shear = 0.7*16700 = 11690 psirnner f i l let vreld in shear = O.49*L6700 = 8183 psi
Strenat'h of we]-ded joints:
3 .12 .L996;Doc No. V49-l-{74
Pase 14 of3E
N1-1ST ROV{-CHgTER
(1) Inner fil1et weLd in shear(P i l 21*11s t t1e O .D . *Leg*S i = 1 . 5 7 i I * 0 . 2 5 * 8 l - I 3 = 25694 .62 1 -b f
(3) Nozzle wal l in shear(P i /2 ) *Mean nozz l .e d ia . * tn *sn = L .5 '7 *7 .75*0 .25* ] -1690 = 35559 .52 1b f
(4) Groove weld in tension(P i /Z '1 *11s r r1e O .D . * t v r *Sg = 1 .57*8*0 .1875*12358 = 29103 .09 l b f
Loadinq on welds per IKi-41 (b) (1)
w = (a - (d - 2 * tn ) * (E1* t - F * t r ) ) * sv= ( 1 . 5 8 8 - ( 7 . 5 3 3 - 2 ' , 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) ) * 1 6 7 0 0= 7234 ,131 l b f
W1--1 = (A2 + A5 + A41 + A42) *Sv= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 ) * 1 5 7 0 0= 5 8 7 8 . 4 l b f
W2-2 = (A2 + A3 + A41 + A43 + 2*tn*t* fr1) *Sv= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 + 2 * 0 . 2 5 * 0 . 3 7 5 * 1 ) * 1 5 7 0 0= 9 0 0 9 . 6 s l b f
t oad fo r paEh 1 -1 l esse r o f w o r W1-1 = 5878 .4 l b fPa th 1 -1 T t r ru (1 ) & (3 ) = 25594 .62 + 35559 .52 = 6L254 .14 1b fPath 1-1 is stronger than WL-l- so i t is acceptable per UG-41(b) (1).
Load for p'aEh 2-2 lesser of W or W2-2 = 7234.L3L l-bfPa th 2 -2 Thm (1 ) , (+ ) = 25694 .62 + 29103 .O9 = 54797 .71 l b fPaE!-r 2-2 is stronger than w so i t . is acceptable per Uc-41(b) (2).
Reinforcement Ca]-cul-ations For l{ozzle lrlAP
Limits of reinforcement IE-40
Paral le l t ,o the vessel wal l d = 7.533 inNormal to the vessel waI l outside 2.5* ( tn-Cn) + Ce = .625 inNorma1 to the vessel wal l inside 2.5* ( tn-Cn-C) = .625 in
Deterninat ion of Olord Length
Thetal = ArcCos ( (L,o + RrI) /Rm)= A r c c o s ( ( 7 . 8 7 5 + 3 . 7 5 ) / 8 4 . 3 5 5 4 )= 6 Z . V t > 5 2
TheLa2 = ArcCos ( (r,o - Rn) ,/Rm)= A rccos ( (7 .875 - 3 .7s ) / 84 .3ss4 )= 87 .19758
d = 2*Rm*Sin( (Theta2 - Thetal) /2)= 2 * 8 4 . 3 s 5 4 * S i n ( ( 8 7 . 1 9 7 5 8 - 8 2 . 0 7 9 3 2 ) / 2 )= 1 . 5 3 3 r n
REVO
Doc No. V49-r-074
P!q. 15 of 3E3 . 1 2 . 1 9 9 5
N1-1ST ROW-CEtfrfER
Nozzle resuired thickness
t rn = P* I tn / (Sn*E - 0 .6 *P)= 8 3 . 5 4 0 7 7 * 3 - 7 5 / ( L 6 7 0 0 * 1 - 0 . 6 * 8 3 . 5 4 0 7 7 )= 0 . 0 1 8 8 i n
Required thicloess tr frm IIG-37 (a) {1)
t r = P * L * M / ( 2 * S * E - 0 . 2 * P )= 83 .54077* 84 .25*a / (2 *a67OO*7 - 0 .2 *83 .54077)= 0 . 2 1 0 8 i n
Area reouired
Al1owab le s t resses ; Sn = l .6700,
f r1 = lesser o f 1or Sn/Sv so f r1fr2 = lesser of L or Sn,/Sv so fr2
Sv = 1-5700, ps i
A = d* t r *F + z* tn* t r *F* (1 - f r1 )= 7 . 5 3 3 * 0 . 2 1 0 8 * l _ + 2 * 0 . 2 5 * 0 . 2 1 0 8 * 1 * ( 1 - 1 )= 1 . 5 8 8 i n ^ 2
Area av-ai1allle
A1 = larger of the foflowing = a -237 i.n^ 2
= d* (E1* t -F * t r ) - 2 t t n * (E1* t -F * t r ) * (1 - f r1 )= 7 . 5 3 3 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 I ) * ( 1 - 1 )= L .237 !n^2
= 2* ( t+ tn ) * (E1* t -F * t r ) - 2 * tn * (E1*L -F* t r ) * (1 - f r1 )= 2 * ( 0 - 3 7 5 + O . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 L O g ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 I ) * ( 1 - 1 )= . 2 0 5 i n ^ 2
A2 = smaller of the follolvinq = O -289 i-rj^2
= 5* ( tn - t rn ) * f r2* t= 5 * ( 0 . 2 5 - 0 . 0 1 8 8 ) * 1 * 0 . 3 7 5= .433 in^2
= 5* (tn - trn) *fr2*tsn= 5 * ( 0 . 2 5 - O . 0 1 8 8 ) * 1 * 0 . 2 5= . 269 rn Z
A41 = Leg^2*fr2= O . 2 5 ^ 2 * L = . 0 6 3 i n ^ 2
A r e a = A 1 + A 2 + A 4 1= L . 2 3 7 + 0 . 2 8 9 + 0 . 0 5 3= 1 . 5 8 9 i n ^ 2
As Area > A the rei-nforcement is adequate for MAP =
3 .12 .L996
8 3 . 5 4 0 7 7 a E
trTEVOIloc No. V4Il.0?4P.ce 16 ofSt
70 Deg F
N-1- 1ST ROW-CBIrBR
^ Reinforcement check in the p1ane para]-]-el to the long. axistt - Area reourreo
A = d * t r *F + 2 * tn * t r *F* (1 _ f r1 )= 7 . 5 * 0 . 2 1 0 8 * 1 + 2 * O . 2 5 * 0 . 2 1 0 9 * 1 * ( 1 _ 1 )= l - . 581 i n^2
Area availalrle
Al- = f arger of the f ollor.ring = 1.231 in^2
= d * (E l * t -F * t r ) - 2 * tn * (E l * t -F * t r ) * (1 - f r1 )= 7 . 5 * ( l _ * 0 . 3 7 5 - 1 - * 0 . 2 1 0 8 ) - 2 * 0 . 2 5 * ( L * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) * ( 1 - 1 )= t . 23L L t ^2
= 2 * ( t+ tn ) * (81* t -F * t r ) - 2 * !n * (81* t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) * ( L - 1 )= -205 j-n^ 2
Area = A1 + A2 + A4l-= 1 . 2 3 L + 0 . 2 8 9 + 0 . 0 5 3= 1 . 5 8 3 i n ^ 2
As Area > A Lhe reinforcement is adequate for MAP = 83.54Q77 at 70 Deg F
eheck the selds - Fron lll{- 16 (d) :
tm in = lesser o f 0 .75 or tn o r t , tm in = 0 .25 int1 o r t2 (min) = lesser o f 0 .25 or o .7* tmin , t1 (min) = 0 .175 int 1 ( a c L u a l ) = 0 . 7 * L e g = 0 . 7 * 0 . 2 5 = 0 . 1 7 5 i nt2 (acEua l ) = 0 .1875 int ,1 + t2 = 0 .3525 >= 1 .25* tmin
The weld sizes for t1 and t2 are sat.isfactory.
ItG-45 Nozz]-e lileck lbiclsress Check
WaI1 th ickness per UG-45(a) : t r l - = 0 .0188 in (E = 1)waI I th ickcess per UG-45(b) (1 ) : Er2 = 0 .2108 inWal I th ickness per UG-15(b) : t r3 = 0 .0525 inStd p ipe wa1 l per UG-as(b) (4 ) : t r4 = 0 .28175 inThe greater of tr2 or Er3: trs = 0.2108 inThe lesser o f E t4 o r t r5 : t r5 = 0 .2108 in
Req'd per UG-45 is the larger of tr1 or tr6 = 0.2108 in
Awailable nozzLe wall lhickness new. tn = 0.25 in
The nozzle neck tshickness is adequate for MAP.
Allowable stresses in joints IK-45 (c) and llll-15 (c)
REVODo€ No. V49.1474P.@ 17of38
3 -12 .1996
I[1-1ST ROW-CHITER
eroove wel-d in tension = 0.74*76700 = l -2358 psiNozz le wa l l i n shea r = 0 .7 *16700 = 11690 ps iInrrer f i lLets weld in shear = o.49*L67O0 = 8183 psi
Strengrth of welded joints:
(1) Inner f i1 let weld in shear( P i l 2 ) * N o z z l e O . D . * L e g * S i = 1 . 5 7 * 8 * 0 . 2 5 * 8 1 8 3 = 2 5 6 9 4 . 6 2 ] - b f
(3) Nozzle wal1 in shear(P i l 2 ) *Mean f t ozz le d ia . * tn *sn = ! . 51*7 .75*0 .25*11690 = 35559 .52 l b f
(4) Groowe weld in tension( P i / 2 ) * N o z z l e O . D . * t w * S g = 1 . 5 7 * 8 * 0 . 1 8 7 5 * 1 2 3 5 8 = 2 9 1 0 3 . 0 9 1 b f
Loading,on welds oer UG-41 (b) (1)
W = (A - (d - 2 * tn ) * (E1* t - F * t r ) ) *Sv= ( 1 . 5 8 8 - ( 7 . 5 3 3 - 2 * 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 8 ) ) * 1 5 7 0 0= ' t 234 .131 l b f
W1-l- = (A2 + 45 + A41 + A42)*Sv= ( 0 - 2 8 9 + 0 + 0 . 0 6 3 + 0 ) * 1 5 7 0 0= 5 8 7 8 . 4 1 b f
w2-2 = (A2 + A3 + A41 + A43 + 2*tn*t* fr l ) *Sv= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 + 2 * 0 . 2 5 * 0 . 3 7 5 * 1 ) * 1 6 7 0 0= 9 0 0 9 . 5 5 l b f
Load fo r pa th 1 -1 l esse r o f w o r W1-1 = 5878 .4 l b fPath 1-1 rhnr (1) & (3) = 25694.62 + 35559.52 = 51254.14 1bfPath 1-L is stronger than w1-1 so i t is acceptable per UG-41(b) (1) '
Load for paEh 2-2 lesser of w or W2-2 = 7234.131 lbfPaEh 2 -2 thm (1 ) , G) = 25694 .62 + 29L03 .O9 = 54797 .71 1b fPaE]n 2-2 is st.ronger than w so it is acceptable per UG-41 (b) (2) -
Reinforcement Calculations for E:rternal Pressure
LiEits of re inf orc€ment Ire-40
paraLlel to the vessel waII d = 2.533 inNormal to the vessel waI l outside 2.5* ( tn-Cn) + te = .625 inNormal to the wessel wal1 inside 2.5* ( tn-Cn-C) = .525 in
Determinat iofr of Chord Length
Thetal = Arccos ( (Lo + nn) /Rm)= A r c C o s ( ( 7 . 8 7 5 + 3 . 7 5 ) / 8 4 . 3 8 8 8 5 )= 8 2 . 0 8 2 4 8
Theta2 = Arccos( (Lo - PrI) /Rn)= A r c c o s ( ( 7 . 8 7 5 - 3 . 7 5 1 l 8 4 . 3 8 8 8 5 )
REVODoc No. v4q{)74P.ee 18 of383 .L2 -L996
NT-IST ROW- EHTTR.
= 87 .L9869
d = 2*Rm*Sin( (Theta2 - Thetal) , /2)= 2 * 8 4 . 3 8 8 8 5 * S i n ( ( 8 7 . 1 9 8 6 9 - 8 2 . 0 8 2 4 8 | / 2 )= 7 . 5 3 3 i n
Nozzle reouired thickoess
r . , /Do = 3 .39 /8 = .4238 Do /E = 8 /O .OL987 = 402 .5 !7F rom tab le G : A = 0 .000401From tsab1e HA-3: B = 4785.4
Pa= 4*B/ ( 3*Dolt)= 4 * 4 7 8 5 . 4 / ( 3 * 8 / 0 . 0 1 9 8 7 )= 1 5 , 8 4 7 6 p s i
Nozz1e required t.hickness trn - .01987 in
Resuired thiclmess tr frdr re-37 (d) (1) = .2777 in
Area required
Al lowab1e stresses: Sn = L47OO, Sv = 14700, psi
f r1 = l esse r o f 1o r Sn /Sv so f r l - =1fr2 = lesser of 1 or Sn/Sv so fr2 -1-
A = 0 . 5 * ( d * t s r * F + z * t n * t r * F * 1 f - f r 1 ) )= 0 . 5 * ( 7 . 5 3 3 * 0 . 2 7 7 7 * L + 2 * O . 2 5 * 0 . 2 7 7 7 * ! * ( 1 - 1 ) )= ! .O45 i l r^ 2
Area avai].able
Al- = Iarger of the fol lowing = .733 in^2
= d * (E1 t t -F * t r ) - 2 *g r l * (E1* t -F * t r ) * (1 - f r ] . )= 7 . 5 3 3 * ( 1 * 0 . 3 7 5 - l _ * 0 . 2 7 7 7 1 - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 7 7 ) * ( L - 1 - )= .733 in^2
= 2 * ( t .+ tn ) * (81* t -F *Er ) - 2 *Cn* (81* t -F *E . r ) * (1 - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 1 * ( 1 * 0 . 3 ? 5 - 1 * 0 . 2 7 7 7 ) - 2 * 0 . 2 5 * ( 1 - * 0 . 3 ? 5 - 1 * 0 - 2 7 7 1 1 * ( L - ] - )= . ! 22 !n^2
A2 = smal ler of the fol10wing = 0.288 in^2
= 5* ( tn - t rn) * fT2*E= 5 * ( 0 . 2 5 - 0 - o L 9 8 7 ) * 1 - * 0 . 3 7 5= . 4 3 1 i n ^ 2
- 5* ( t .n - t rn) * f r2*tn= 5 * ( 0 . 2 5 - O . 0 1 9 8 7 ) * 1 * 0 . 2 5= .288 i ' -^2
REVODoc No. V49-l{74P.r.19of38
3 . 12 .1996
ITI-1ST ROI| _CffTER
A41 = Leg^2*fr2= 0 . 2 5 ^ 2 * ! = . 0 6 3 i n ^ 2
A r e a = A 1 - + A 2 + A 4 1= 0 . 7 3 3 + 0 . 2 8 8 + 0 . 0 6 3= 1 . 0 8 4 i n ^ 2
As Area > A the reinforcement is adequate for Pe = 15.75347 at 400 Deg F
Reinforcement check in the plane parall-el- to the ]-ong- axis
Area required
A = 0 . 5 * ( d * t r * F + 2 * t n * t r * F * ( 1 _ f r l ) )= 0 . 5 * ( 7 . 5 * 0 . 2 7 " 7 7 * L + 2 * 0 . 2 5 * 0 . 2 1 7 7 * a * ( 1 - 1 ) )= 1 . 0 4 1 3 7 5 i n ^ 2
Area available
41 = Iarger of the following = . 1 3 I n Z
= d* (E1* t -F * t r ) - 2 *g4* (E l * ! -F * t . r ) * (1 - f r ] . )= 7 . 5 * ( 1 * 0 . 3 ? 5 - 1 * 0 . 2 7 7 7 ' ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - l - * 0 . 2 7 7 7 ) * ( I - l . )= .73 !n^ 2
= 2 * ( t+ tn ) * (E1 r . t -F * t r ) - 2 * tn * (81 - * t -F * t . r ) * (1 - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * O . 3 7 5 - 7 * 0 . 2 7 7 7 ) - 2 * 0 . 2 5 * ( 1 - * 0 . 3 7 5 - 1 * 0 - 2 7 7 7 \ * ( L - L )= - I22 i r r^2
A r e a = A 1 + A 2 + A 4 1= Q . 7 3 + 0 . 2 8 8 + 0 . 0 5 3= 1 . 0 8 1 i n ^ 2
As Area > A the reinforcement is adequate for Pe = 15 .76347 at 400 Deg F
Ire-45 lilozzle lteck 'Ilriclmess Check
Wall thickness per UG-45 (a) :WaI1 thickness per UG-45 (b) (2) :Wall Ehickness per UG-15 (b) :Std pipe waII per Uc-45 (b) (a) :T'he greater of Er2 or tr3:The lesser of tsr4 or tr5:
t r 1 = 0 . 0 1 9 8 7 i n ( E = l - )E r 2 = O . 0 4 5 2 i nt r 3 = 0 . 0 5 2 5 i ntr4 = 0 ,28L75 int r 5 = 0 . 0 5 2 5 i nt r 5 = 0 . 0 6 2 5 i n
Req'd per UG-45 is lhe larger of t r l - or t r5 = 0.0625
Availa.bl-e rtozzl�e waII thickness new. tn = 0.25 in
The nozzle neck thickness is adequate for Pe.
REVODoc No. v49-l-o?4Pase 20 of38
3 .12 -1995
II2-1ST ROII-RIGIIT
Ooeninq N2 Reinforcement Calculations Per IIG-37
Located on:User input vessel thickness :Liguid static head included:Flange description:
Nozzle material specif icat ion i
Nozzle orient.at.i.on :End of nozzLe to datum line:Nozzle calculated as hi l ls ide:Proj ection outside vessel- Lpr:
84'I F6D HAM HEAD. 3 7 5 i n0 ps iNot instal led
SA 240 3O4L HIGH
59.7 degreesL6 .752r inyes3 . 0 8 3 i n
tsn ->
< - d - >
*,
tw1->
<- R - r l
Reinforcement Ca].cul-at'ions For Nozzle MAI{P
I,inits of reinforcement lre-40
Para]lel to the vesseL wall d = 7 -787 inNormal to tshe vesseL walL out.side 2.5* (tn-Cn) +Normal to the wessel wall inside 2.5* (tn-Cn-C) =
Deter:uinat ion of Chord Lengrth
Thetal = Arccos ( (l,o + Rn) /Rm)= A r c c o s ( ( 2 2 . 6 6 + 3 . ? 5 ) / 8 4 . 3 5 5 0 5 )= / r - / 5 5 . ' t )
Thera2 = Arceos ( (to - Rn) /Rm)= A r c e o s ( ( 2 2 . 6 6 - 3 . 7 5 ) / 8 4 . 3 5 5 0 5 )= 7 7 . 0 4 6 2 5
d = 2*Rm*Sin( (Theta2 - Thetal_)/2)= 2 * 8 4 . 3 5 5 0 5 * S i n ( ( 7 7 . 0 4 5 2 6 - 7 L . 7 5 5 3 6 ) / 2 )= 7 . 7 8 7 l n
Nozzle required thiclfiess
t r n = P * R n / ( S n * E - 0 . 5 * P )= 8 3 . 2 6 1 3 1 * 3 . 7 5 / ( L 6 7 0 0 * 1 - 0 . 6 * 8 3 . 2 5 1 3 1 )= 0 . 0 1 8 8 i n
3 .L2 _L995
corrosion allow =noz thick new En=r:ozzl-�e id. ner^r d=fi l lets weld tw1 =groove r,'rel-d tw2 =
To head center R=
0 i n. 2 5 i n7 . 5 i n. 2 5 i n. 1 8 7 5 i n
22.56 i rL
t e = . 5 2 5. 5 2 5 i n
an
RXVODo. No. v49-t-0?4
N2-1ST ROW-RIGET
Required thickness tr from UG-37(a) (1)
t r= P* I r *M/ (2 *S*E - 0 .2 *P)= 83 .26131*84 .25*1 - / (2 * l -6700*1 - 0 .2 *83 .26 ] -3a l r= 0 . 2 1 0 1 i n
Area reouired
A f lowab le s t resses : Sn = 16700 , Sv = 16700 , ps i
f rL = lesser of L or Sn/Sw so fr1 =1f r2 = l esse r o f 1o r Sn /Sv so f r2 =1
A = d *g ; *p + 2 * tn * t r *F* (1 - f r 1 )= 7 . 7 9 . 7 * 0 . 2 1 0 1 * 1 + 2 * O . 2 5 * 0 . 2 1 0 1 * 1 * ( 1 - 1 )= l - . 5 3 6 i n ^ 2
Area- available
A1 = l-arger of the following = 1-.284 !n^2
= d* (E l i ( t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 7 . 7 8 7 * ( 1 * 0 . 3 7 5 - 1 - * 0 . 2 L 0 1 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) * ( 1 - 1 )= L .284 !rL^ 2
= 2 * ( t+ tn ) * (E1*E-F* t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r ] - )= 2 t ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 ? 5 - 1 * 0 . 2 L 0 : - ) - 2 * 0 . 2 5 * ( l - * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) * ( l - - 1 )= . 2 0 6 i n ^ 2
A2 = smal ler of the fol lowinq = 0.289 in^2
= 5* ( tn - t rn) * f r2*t= 5 * ( 0 . 2 5 - 0 . 0 1 8 8 ) * 1 * 0 . 3 7 5= . 4 3 3 i n ^ 2
= 5 t ( t n - t r n ) * f r2 * tn= 5 i . ( 0 . 2 5 - 0 . 0 1 8 8 ) * 1 * 0 . 2 5= .289 in^2
A41 = L,eg^2*fr2= o . 2 5 ^ 2 * 1 _ = . 0 5 3 i n ^ 2
A r e a = A 1 + A 2 + A 4 1= L . 2 8 4 + 0 . 2 8 9 + 0 . 0 5 3= 1 - . 5 3 5 i n ^ 2
As Area > A the reinforcement is adequate for MAWP = 83.26L31 at 0 Deg F
Reinforcement check in the ptane para].le]- to the long- axis
Area reanrired
U A = d * t r *F + 2 * tn * t r *F* (1 - f r 1 )
REVO
Doc No. V49-1.074
P.a 22. f38
3 . L 2 . L 9 9 5
il2_1ST ROI{_RIGIIT
= 7 . 5 * O . 2 1 0 1 * 1 + 2 * 0 . 2 5 * O . 2 1 0 1 _ * L * { 1 - 1 )= 7,57575 j . r '^ 2
.Area awailable
A1 = larger of the following = L.237 r-n^2
= d* (81*E_F* t r ) _ 2 * tn * (E l * t_F*Er ) * (1_ f r1 )= 7 . 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 L 0 1 - ) * ( 1 - 1 )= 7 .237 i n^ 2
= 2 * ( t + t n ) * ( E 1 * t - F * t r ) - 2 * t n * ( E 1 * t - F * t r ) * ( 1 - f r 1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - l - * 0 . 2 1 - 0 L ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) * ( 1 - 1 )= .206 !n^2
Area = A1 + A2 + .A,41= L , 2 3 7 + 0 . 2 8 9 + 0 . 0 5 3= 1 . 5 8 9 i n ^ 2
As Area > A the reinforcement is adequate for MAWP = 83.26131 at 0 Deg F
eheck the welds - Frun IfW-16(d):
tm in = lesser o f 0 .75 or Ln or t , tm in = 0 .25 inEL or E2 (min) = lesser o f 0 .25 or 0 .?* tmin , t l (m in) = 0 .175 int 1 ( a c L u a l ) = o . ? * L e g = 0 . 7 * 0 . 2 5 = 0 . a 7 5 i r Lc2 (ac tua l ) = 0 .18?5 int 1 + t , 2 = 0 . 3 6 2 5 > = 1 . 2 5 * t m i n
The weld sizes for tL and t2 are satisfactorv.
Ire-45 Nozzle l{eck lhickness Check
Wal l th ickness per UG-45(a) : Er ] . = 0 ,0188 in (E = 1)wa l I Lh ickness per uG-45(b) (1 ) : t r2 = 0 .2101 inwa11 th ickness per UG-16(b) : t r3 = 0 .0625 ins td p ipe wa l1 per I IG-as(b) (4 ) : t s r4 = 0 .28175 inThe greaEer of tr2 or tr3: Er5 - 0.2101 inThe l"esser of tsr4 or tr5: tr6 = 0.2101 in
Reqtd per UG-45 is the larger of trL or tr5 = 0.2101 in
Available nozzle wa1l chickness new, tn = 0.25 in
The nozzle neck thickness is adequate for MAWP.
Al lrrsable stresses in ioints [tcl-4s (c) and {1If-15 (c)
Groove weld in Lension = o.74*!67Q0 = l -2358 psiNozzLe wa l ] i n shea r = 0 .7 *15700 = 11690 ps iInner f i l let weld in shear = Q.49*L67O0 = 8183 psi
Strengrth of welded joints :
3 - !2 -L995REVO
Doc No. V4!1{74
Prpe 23 of 38
N2-1ST ROW-RTGHI
(1) I rmer f i l let weld in shear(P i / z ) *Nozz le O .D . *Leg*S i = 1 . 5 7 * I * 0 . 2 5 * I 1 8 3 = 25594 .62 l b f
(3) Nozz1e wa1I in shear(P i l 21*1v1 . " t t nozz l -e d ia . * tn *Sn = L .57*7 .75*0 .25*11690 = 35559 .52 l b f
(4) Groowe wefd in tension( P i / 2 ) * t t o z z l - e O . D . * t w * S g = 1 . 5 ? * 8 * 0 . 1 8 7 5 * 1 2 3 5 8 = 2 9 1 0 3 . 0 9 l b f
Loading on weLds frer IN;-41 (b) (1)
W = (e - (d - 2 * tn ) * (E l - * t - F *L r ) ) *Sv= ( 1 . 6 3 6 - 1 7 . 7 8 7 - 2 " O . 2 5 \ * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) ) * 1 6 7 0 0= 7254 .041 l b f
W 1 - 1 = ( A 2 + A 5 + A 4 1 + A 4 2 ) * 5 t= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 ) * 1 6 7 0 0= 5 8 7 8 . 4 l b f
W2-2 = (A2 + A3 + A41 + A43 + 2*tn*t* fr1) *Sv= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 + 2 * 0 . 2 5 * 0 . 3 7 5 * L ) * 1 5 7 0 0= 9 0 0 9 . 5 5 l b f
L,oad for path 1-1 l -esser of W or W1-1 = 5878.4 lbfPa th 1 - -1 Th ru (1 ) c (3 ) = 25694 .62 + 35559 .52 = 6L254 .14 l b fpath L- l - is st rong'er than w1-1 so i t is acceptable per UG-41 (b)(1).
Load for pat} f 2-2 lesser of W or W2-2 = 7254.041 lbfpa t } ] 2 -2 r t u r r (1 ) , ( 41 = 25694 .62 + 29103 .O9 = 54797 .71 l b fPat}J 2-2 is stsrongier than w so it' is acceptsable per UG-41 (b) (2).
Reinforcement Calculations For Nozzle MAP
Linits of reinf orcement UG-4O
Paral le l Eo lhe wessel wa1l d = 7.787 LrtNormat Co the vessel waI] outside 2,5* ( tn-Cn) + te = .525 inNormal to the vessel wal-L inside 2.5* ( tn-Cn-C) = .525 in
Determinats ion of Chord Leaqth
Ttretal = ArcCos ( (Lo + Rn) /Rm)= A r c C o s ( Q 2 . 5 6 + 3 . ? 5 ) / 8 4 . 3 s 4 e ' )= 7 r . 7 5 5 3
T'heta2 = Arccos ( (r.,o - Rn) /Rm)= A r c c o s ( ( 2 2 . 6 6 - 3 . 7 5 ) / e 4 . 3 5 4 8 )= 7 7 . 0 4 6 2 2
d = 2*Rm*Sin( (Tl leta2 - Thebal) /2)= 2 *84 .3548*S in ( (7? .04622 - 7L .1553) /2 )= 7 . 7 8 7 i n
R?VODoc No, V4rr.07{
3 - 12 .1996
N2-1ST ROI{-RIGET
llozzle recuired thickness
t r n = P * R n / ( S n * E - 0 . 6 * P )= 8 3 . 0 6 7 4 6 * 3 . 7 5 / ( L 6 7 O O * 1 - 0 . 5 * 8 3 . 0 5 7 4 5 )= 0 . 0 L 8 7 i n
Required thickness tr frqn UG-37(a) (1)
t r = P * L * M / ( 2 * S * E _ 0 . 2 * P )= 8 3 - 0 6 7 4 6 * 8 4 . 2 5 * L / ( 2 * 1 5 7 0 0 * 1 - 0 . 2 * 8 3 . 0 6 7 4 5 )= 0 . 2 0 9 6 i n
Area reouired
Al lowab1e stresses: Sn = i -5700, Sw = 15766, psi
f r1 = l esse r o f 1o r Sn /Sv so f r1 =1f r2 = Lesse r o f 1o r Sn /Sv so f r z =1
A = d*tr*F + 2*tn*tr*F* (1 _ fr j_)= 7 . 7 8 7 * 0 . 2 0 9 6 * 1 + 2 * 0 . 2 5 * 0 - 2 O 9 6 * t * ( 1 _ 1 )= L . 6 3 2 2 ! n ^ 2
Area anrailable
A1 = larger of the following = 1 _ . 2 8 8 i n ^ 2
= d * (81* t -F * t . r ) - 2 *91* (E1* t -F * t , r ) * (1 - f r1 )= 7 . 7 8 7 * ( 1 - * 0 . 3 7 5 - 1 ' r 0 . 2 0 9 6 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 6 ) * ( 1 - 1 )= 1 . 2 8 8 i n ^ 2
= 2 * ( t+ tn ) * (81* t -F * t r ) - 2 * tn r . (E1* t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 6 . 3 7 5 - 1 * 0 . 2 0 9 6 \ _ 2 * O . 2 5 * ( L * 0 . 3 7 5 _ 1 * 0 . 2 0 9 6 ) *= .2O7 !n^2
A2 = smaller of the foll-owing
= 5* (tn - trn) t fr2*E= 5 * ( 0 . 2 5 - 0 . 0 1 8 7 ) * 1 * 9 . 3 7 5= .434 in^ 2
= 5* ( tn - t rn ) * f r2* tn= 5 * ( 0 . 2 5 - 0 . 0 1 8 7 ) * . 1 * 9 . 2 5= . Z d 9 l l l Z
A41 = Leg^2 *fr2= 0 . 2 5 ^ 2 * r = . 0 5 3 i n ^ 2
A r e a = A 1 + A 2 + A 4 1= 1 . 2 8 8 + 0 . 2 8 9 + 0 . 0 6 3= t .64 i r .^ 2
As Area > A the reinforcement is adequate
3 . L 2 - L 9 9 5
= 0 . 2 8 9 i n ^ 2
( 1 - 1 )
83 . 067 45
REVO
Doc No. V49l{74
for MAP =
N2-1ST RO�T-RTGET
|l Reinforcement check in che plane para]-le]- to the long - axis-
Area required
A = d * t r *F + 2 * tn * t r *F* (1 - f r 1 )= 7 . 5 * 0 . 2 0 9 6 * 1 + 2 * 0 . 2 5 * 0 . 2 O 9 6 * L t ( 1 _ 1 )= L .s72 i -n^ 2
Area avai]-alr].e
A1 = larger of the foJ-lowing = f .24 in^2
d* (81* t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )7 . 5 * ( 1 * 0 . 3 7 5 - 1 - * 0 . 2 0 9 6 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 5 ) * ( 1 - 1 )L . 2 4 ! n ^ 2
2* ( t+ tn ) * (81* t -F * t r ) - 2 * t r f * (E1* t -F * t r ) * (a - f r l )2 * ( 0 . 3 ? 5 + 0 . 2 5 ) * ( 1 i . 0 . 3 7 5 - 1 * O . 2 0 9 6 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 5 ) * ( 1 - 1 ). 2 0 7 ! n ^ 2
A r e a = A l - + A 2 + A 4 1= L . 2 4 + 0 . 2 8 9 + 0 . 0 6 3= 1 . 5 9 2 i n ^ 2
As Area > A tshe reinforcemen! is
Ctreck the welds - Fror U$I-16(d):
lmin = lesser of 0.75 or tn or t ,t1 o r t2 (min) = Lesser o f 0 .25 ort 1 ( a c t u a l ) = 0 . 7 * L e g = 0 , 7 * 0 . 2 5 =t2 (ac tua l ) = 0 .1875 int 1 + 1 2 = 0 . 3 6 2 5 > = 1 . 2 5 * t m i n
The weld sizes for t1 and E2 are
IK9-45 lilozzle Neck lbicloess freck
wall thickness per UG-45 (a) :wa11 thickness per IrG-a5(b) (1) :WalI tshickness per UG-15 (b) :SEd p ipe wa l l per UG-as(b) (a ) :The greater of tr2 or tr3:T'h.e lesser of tr4 or tr5 :
adequate for MAP = 83.06746 at. 70 Deg F
Lmin = 0 .25 in0 .7 * tm in , t 1 (m in ) = 0 .175 i n0 . 1 7 5 i n
satsisfactory.
Regr d per UG-45 is the larg'er of !r1-
Awailable rr.ozz].�e waLl thickness new,
t r 1 = 0 . 0 1 8 7 i n 1 g = 1 )t r2 = 0 .2095 i -nt r 3 = 0 . 0 5 2 5 i nt r 4 = 0 . 2 8 1 7 5 i nt , r 5 = 0 . 2 0 9 5 i nt r 6 = 0 . 2 0 9 5 i n
o r t r 6 = 0 . 2 0 9 5 i n
t n = 0 - 2 5 i n
TLre nozzle neck thickness is adequate for MAP.
A1]-owable stresses in joiats UG-45 (c) and tttf-ls (c)
3 -]-,2 -L996Doc No. V49-r-074
oN2-1ST ROW-RIGST
Groove weld in tension = O.74*167O0 = 12358 psiNozz1e wa l l i n sbea r = 0 .7 *1d200 = 11690 ps iInner f i l l -et . weld in shear = 0.49*l-6700 = 8183 psi
Strength of nelded joints:
(1) Inner f i lLet weld in shear(P i /2 ) *Nozz le O .D . *Leg*S i = 1 .57*8*0 .25*8183 = 25694 .52 l b f
(3) Nozzle wal l in shear(P i l 21 *1 ,1 " . t t nozz le d ia . * t n *Sn = L -57*7 .75*0 .25* j . 1690 = 35559 .52 l b f
(4) Groowe we]d in tension( P i / 2 ) * N o z z T e O . D . i . t w * S g = 1 . 5 7 * 8 * 0 . 1 8 7 5 * 1 2 3 5 8 = 2 9 1 0 3 . 0 9 t b f
Loading on relds per lre-41 (b) (1)
w = (A - (d - 2 * t , n ) * (81* t - F * t r ) ) *Sv= ( L . 6 3 2 2 - ( 7 . 7 8 7 - 2 * 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 6 ) ) * 1 5 7 0 0= 7729. '734 l_bf
W 1 - 1 = ( A 2 + A 5 + A 4 1 + A 4 2 ) * S v= ( 0 . 2 8 9 + 0 + 0 . 0 5 3 + 0 ) * 1 5 7 0 0= 5 8 7 8 . 4 l b f
W2-2 = (A2 + A3 + A41 + A43 + 2 * tn * t * f r1 ) *Sv= ( 0 . 2 8 9 + 0 + 0 . 0 5 3 + 0 + 2 * 0 . 2 5 * 0 . 3 7 5 * 1 ) * 1 6 7 0 0= 9 0 0 9 . 6 5 l b f
Load for path 1--L lesser of W or ! i l1- 1- = 58?8.4 lbfPa th 1 -1 Th ru (1 ) & (3 ) = 25694 .62 + 35559 .52 = 6L254 .14 l b fPath 1-1 is stronger than W1--1 so it is acceptable per Uc-41- (b) (1) .
Load for path 2-2 lesser of w or W2-2 = 7129.734 IbfPaEh 2 -2 Th ru (1 ) , @l = 25694 .62 + 29103 .O9 = 54797 .71 l b fPaE}: 2-2 is stronger than W so i t is acceptable per UG-41(b) (2).
Reinforcement ea]-cu]-ations for B(tenral Pressure
Limits of re inforcement tIG-40
Paral le l tso the vessel walI d = 7.187 tnNormal to the vessel walI outside 2.5* ( tn-Ch) + te = .525 inNorma1 tso the vessel wal l inside 2.5* 1tn-Cn-C) = .525 in
Determinat ion of ebord Lenqth
Thetal = Arccos((Lo + Rn), /Rm)= A rccos ( (22 -66 + 3 .75 ) / 84 .38945)= / r . / a . l U o
Theta2 = Arccos ( (r,o - Rn) /Rm)= ArcCos ( G2 .65 - 3 .7s) /84 .38945)
REVODoc No. V4qt474
3 .L2 .7 -996
N2-1ST ROW-RTGHT
= 77 .O5L63
d = 2*Rm*Sin( (Theta2 _ Thetal) /2)= 2 * 8 4 . 3 8 9 4 5 * S i n ( ( ? 7 . 0 5 1 6 3 - 7 L . 7 5 3 0 6 ) / 2 )= 7 . 7 8 7 i a
Nozzle reguired thicl,rness
r . , /Do = 3 .083 , /8 = .385a Do /E = 8 /O .Oa962 = 4O7 .7472From tab fe G : A = 0 .000437From tab le IA -3 : B = 4858 .3
Pa= 4*B/ ( 3 *Do/t )= 4 * 4 8 5 8 . 3 / ( 3 * 8 / O . O L 9 6 2 )= 1 5 . 8 8 5 6 p s i
Nozzle required thickness t,rn = .01952 in
Required thickness tr from ItG-37 (d) (1) = -2789 in
Area realired
Al- lowable stresses: Sn = l -4700. Sv = 14700, psi
f r1 = l esse r o f 1o r Sn /Sv so f r1 =1fr2 = l -esser of 1 or Sn/Sv so fr2 =1
A = 0 . 5 * ( d * E r * F + z * t n * t r * F * ( 1 - f r 1 ) )= 0 . 5 * ( 7 . 7 8 7 * 0 . 2 7 8 9 * ! + 2 * 0 . 2 5 * 0 - 2 7 8 9 * L * ( 1 - 1 ) )= 1 . 0 8 5 9 i n ^ 2
= .748 i n^2
Area available
A1 = larger of the following
= d* (E l * t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 7 - 7 8 7 * ( 1 * 0 . 3 7 5 - 1 r . 0 . 2 7 8 9 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - t * 0 . 2 7 8 9 1 * ( t - - 1 )= -748 irt^Z
= 2 * ( t+ tn ) * (E l * t , -F * t r ) - 2 * t ' n * (E l_ * t s -F* ! r ) * (1 - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 7 8 9 , - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * J 0 . 2 7 8 9 ) * ( L - r )= -!2 j-n^ 2
A2 = smaller of E,he following
= 5* (t.n - tsrn) *frz*E= 5 * ( 0 . 2 5 - 0 . 0 1 9 5 2 ) * 1 * 0 . 3 7 5= -432 in^ 2
= 5* (t ,n - trn) *fr2*t.n= 5 * ( 0 . 2 5 - 0 . 0 1 9 6 2 ) * t * O . 2 5= . 2 8 8 i n ^ 2
= 0 . 2 8 8 i n ^ 2
Rf,VODoc tr{o. V49-l-0743 .42 .L995
I[2 - 1ST ROW-RIGIIT
A41 = Leg^2*fr2= 0 . 2 5 ^ 2 * L = . 0 6 3 i n ^ 2
As Area > A the reinforcement is adequate for Pe = L5.82647 at 400 Deg F
Reinforcements check in the plane para]-].e]- !o the long. axis
Area reguired
A = 0 . 5 * ( d i t r * F + 2 * t n * t r * F * ( 1 - f r 1 ) )= 0 . 5 * ( 7 . 5 * 0 . 2 7 8 9 * 1 , + 2 * 0 . 2 5 * 0 . 2 7 8 9 * 1 - * ( 1 - 1 ) )= 1 . 0 4 5 8 7 5 i n ^ 2
Area available
A1 = larger of the following = .72! ilf^ 2
d* (E1* t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f I 1 )7 . 5 * ( ! * 0 . 3 7 5 - 1 - * 0 . 2 7 8 9 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - l - * 0 . r r g 9 1 * ( ] - - L ).72L i r !^ 2
2* ( t+ tn ) * (81*C-F* t r ) - 2 * tn * (81* t -F * t r ) * (1 - f r1 )2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 7 8 9 ) - 2 * O - 2 5 * ( L * 0 . 3 7 5 - 1 *o . 2 7 8 9 ) * ( 1 - 1 ).L2 in^ 2
Area = A1 + A2 + A41-- Q . 7 2 L + 0 . 2 8 8 + 0 . 0 5 3= L.072 j-r:^ 2
As Area > A the reinforcement is adequate for Pe =
Ire-45 ltozzle lveck lllicloess eheck
Area = A1= O . 7 4 8= L . V J J
+ 4 2 + A 4 1+ 0 . 2 8 8 + 0 . 0 5 3j.n^2
L5 .826
wall thickness per UG-45 (a): tr1 = 0.01-952 in (E =walL th ickness per I IG-45(b) (2 ) : |L r2 = Q.0454 inWal l Eh ickness per UG-16(b) : t r3 = 0 .0625 inStd pipe wal- l- per UG-as (b) (a): tr4 = 0 .28L75 inThe greater of t t2 or t .r3: tr5 = 0.0525 inThe lesser of tr4 0r tsrs: t '16 = 0.0625 Ln
Req'd per UG-45 is the larger of tr1 or tsr5 = 0.0525 in
Available nozzle wal1 thickness new, tn = 0.25 in
The nozzle neck thickness is adequate for Pe-
47 aE 400
1 )
Deg F
REVODoc No. Y,l9-l-0743 . L 2 . L 9 9 6
N4-2ND ROT|-RIGHT
Opening N4 Reinforcetr€nt Calculations Per ItG-37
Located on:User input vessel thickness :Liquid static head included:Flange description:
Nozzle material specif icat ion:
Nozzle orientat ion:End of nozzl-e to datum line:Nozzle calculated as hi l ls ide :Project ion outside vessel Irpr:
84II F&D HAM HEAD. 3 7 5 i n0 ps iNot installed
SA 240 3O4L HIGH
28.03 degrees1-6 .627 9 LtLz - "3 . 0 5 7 i n
tw1->< - d - >
*,
!n ->
c o r r o s i o n a l l o w = 0 i nnoz thick new tn= .25nozzl-e id. new d= Z . 5f i l l e t we ld tw1 = .25
anl_n
l-n
groove weld Ew2 = .L875 i{[
< - R - t l To head cencer R= 23.01- r.n
Reinforcement calculations For Nozzle uAwP
Limits of reinforcenent ItG-40
Paral-Lel to the vessel waII d = 7.796 inNorrnal Lo tshe wessel wal l out.s ide 2,5* ( tn-Cn) +Normal to lhe vesser vqal l inside 2.5* ( tn-cn-c) =
Deterflination of Chord LenaEh
Thetal = ArcCos ( (to + Rn) /Rm)= A r c e o s ( ( 2 3 . 0 1 + 3 . 7 5 ) , / 8 4 . 3 5 5 0 s )= 71_.50487
Theta2 = Arccos ( (Lo - Rn) /Rm)= A r c c o s ( ( 2 3 . 0 1 - 3 . 7 5 1 / 8 4 . 3 5 5 0 5 )= 76 .8022
d = 2*Rm*Sin( (Ttreta2 - TheEal) /2)= 2 * 8 4 . 3 5 5 0 5 * S i n ( ( 7 6 . 8 0 2 2 - 7 L . s O 4 8 7 ) / 2 )= 7 . 7 9 6 L n
l{ozzle reouired thickness
t rn = P*Rn / (Sn*E - 0 .5 *P)= 8 3 . 2 5 1 3 1 * 3 . 7 5 / ( 1 6 7 0 0 * 1 - 0 . 5 * 8 3 . 2 6 L 3 1 )= 0 . 0 1 8 8 i n
3 . L 2 . L 9 9 6
t e = . 6 2 5.625 Ln
N4-2I[D ROW-RIGET
Required thickness tr froltr Uc-37 (a) (1)
t r = P * L * M / ( 2 * S * E - 0 . 2 * P )= 8 3 . 2 6 1 3 1 * 8 4 . 2 5 x L / ( 2 * ! 6 7 O j * t - 0 . 2 * 8 3 . 2 6 L 3 L )= 0 . 2 1 " 0 1 i n
Area resuired
A l l owab le s t resses : Sn = 16700 , Sv = 15700 ,
f r l = l esse r o f 1o r Sn /Sv so f r ] . =1fr2 = lesser of 1 or Sn/Sv so fr2 =1
A = d*tsr*F + 2*tn* lr*F* (1 _ fr1)- 7 . 7 9 6 * 0 . 2 1 0 1 * 1 + 2 * 0 . 2 5 * 0 . 2 a Q L * L * ( 1 - 1 )= a.6379 j -rr^2
Area availabl-e
A1- = larger of the following = 1 - .286 i n^2
= d * (E1* t -F * t . r ) - 2 *91 r . (gJ . * t -F * t r ) * (1 - f r1 )= ' 7 . 7 9 6 * ( 1 - * 0 . 3 7 5 - 1 _ * 0 . 2 1 0 L ) - 2 * 0 . 2 5 * ( 1 r . 0 . 3 ? 5 - 1 * 0 . 2 1 0 1 ) * ( 1 - 1 )= L .286 j-r!^ 2
- 2 * ( t+ t sn ) * (E1* t -F * t , f ) - 2 * tn * (E1* t -F * t r ) * ( l _ - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 r . 0 . 3 ? 5 - 1 * 0 . 2 1 0 1 ) - 2 * 0 . 2 5 * { 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) * ( 1 - 1 )= .2O5 Ln^2
A2 = smal ler of the fol l0wing = 0.289 in^2
= 5 * ( t n - t r n ) t f r 2 * t= 5 * ( 0 . 2 5 - 0 . 0 1 8 8 ) * 1 * 6 . 3 7 U= . 4 3 3 i n ^ 2
= 5* ( tn - t rn ) * f r2* tn= 5 * ( 0 . 2 5 - O . 0 1 8 8 ) * 1 * 6 . 2 5= . l 6 Y L n Z
A4]- = Leg^ 2*fr2= o . 2 5 ^ 2 * 1 _ = . 0 6 3 i n ^ 2
A r e a = A 1 + A 2 + A 4 1= 7 . 2 A 6 + 0 . 2 8 9 + 0 - 0 6 3= 1 . 6 3 8 i n ^ 2
As Area > A the reinforcement is adequate for MAWP = 8 3 . 2 6 1 3 1 a t 0 D e g F
Area required
A = d * t r *F + 2 * tn * t r *F* (1 _ f r1 )
3 . L 2 . L 9 9 6 Rf,VpDoc No. V491.{t74
N4 - 2I[D ROTT-RIGHT
= 7 . 5 * 0 . 2 1 0 1 * 1 + 2 t 0 . 2 5 * 0 . 2 1 0 1 * 1 * ( 1 - 1 )= L.57575 j -n^ 2
Area available
A1 = Iarger of the fol lowing = L,237 i^^ 2
= d * (81* t . -F * t r ) - 2 * tn * (E1* t . -F * t r ) * (1 - f r1 )- - 7 . 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) - 2 * 0 . 2 5 * ( 1 - * 0 . 3 7 5 - 1 * 0 . 2 1 0 L ) *= L .237 i n^ 2
= 2 * ( t+En) * (81* t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 1 0 1 ) - 2 * O - 2 5 * ( 1 * 0 . 3 7 5 - 1 *= .205 i -n^2
A r e a - A 1 + A 2 + A 4 1- - L . 2 3 7 + 0 . 2 8 9 + 0 . 0 5 3= 1 - 5 8 9 i n ^ 2
As Area > A Che reinforcemen! is adequate for MAWP =
eheck the relds - From IlI9- 16 {d) :
tm in = 0 .25 in0 .7* tmin . t1 (min)0 . 1 7 5 i n
0 . 2 1 0 1 ) * ( 1 - 1 )
131 ats 0 Deg F
0 . 1 7 5 i n
v49-1.0?4
8 3 . 2 6
tmin = lesser o f 0 ,75 or tn o r t ,t1 o r t2 (min) = lesser o f 0 .25 ort l ( a c t u a l ) = 0 . 7 * L e g = 0 . 7 * 0 . 2 5 =t2 (ac tua l ) = 0 .1875 int 1 + t 2 = 0 . 3 6 2 5 > = L . Z 5 * t m i n
The wefd sizes for t1 and t2 are satisfactory.
[re-45 Iilozzle Neck Tllic]oess eheck
WalI thickness per UG-45 (a) :Wall thickness per UG-as(b) (1) :Wall thickness per UG-15 (b) :Std pipe wall per UG-45 (b) (a) :The gireater of tr2 or tr3:Tlre fesser of t,r4 or tr5:
Req' d per ItG-45 is the larger of t,r1
Awailable rozz]-e wall thickness new,
= 0 . 0 1 8 8= 0 . 2 L 0 1= o . 0 6 2 5= O.28L75= 0 . 2 1 0 1= 0 .21OL
i n / E -
l-nan
t_nl_n1 Y l
tr1Et2t13l ] . /1
tr5Er6
or t r 5 = 0 . 2 1 0 1 i n
= 0 . 2 5 i n
The nozzle neck thickness is adequate for MAWP.
Allowable stresses in ioints Uc-45 (c) and ltw-15 (c)
Groove weld in tension = o.74*!6700 = l -2358 psiNozz le wa l l i n shea r = 0 .? *15700 = l -1590 ps iInner f i l let weld in shear = 0.49*16?00 = 8183 psi
Strenoth of welded joints:
3 .L2 -L996 REVO
Doc Nor
N4 -2IIID ROTI-RIGET
(1) fnner f i . I let weLd in shear( P i / 2 \ * N o z z l e O . D . * L e g * S i = 1 . 5 7 * 8 * 0 . 2 5 * 8 1 8 3 = 2 5 6 9 4 . 6 2 l b f
(3) Nozzle wa1I in shear(P i /Z ; *Mg . r nozz ] �e d ia - * tn *Sn = L .57*7 .75*0 .25*LL590 = 35559 .52 l b f
(4) Groove weld in tension(P i /2 \ *Nozz le O .D . * tw*Sg = 1 .57*8*0 . ! 875*L2358
Ioadinq on welds oer IE-41 (b) (1)
W = (A - (d - z * tn ) * (E1 , t t - F * t r ) ) *Sv= ( r . 6 3 7 9 _ ( 7 - 7 9 6 - 2 * O - 2 5 ) * ( 1 * 0 . 3 7 5= 7260 .986 l b f
W L - 1 = ( A 2 + A 5 + A 4 1 + A 4 2 ) * S v= ( 0 . 2 8 9 + 0 + 0 . 0 5 3 + 0 ) * 1 6 7 0 0= 5 8 7 a . 4 1 b f
w2-2 = (A2 + A3 + A41 + A43 + 2*tn*ts*fr1) isv= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 + 2 * 0 . 2 5 * 0 . 3 7 5 * 1 ) * 1 6 7 0 0= 9 0 0 9 . 6 5 l b f
toad for path 1-1 lesser of w or W1-l- = 5878.4 lbfPa th 1 -1 Thm (1 ) & (3 ) = 25694 .62 + 35559 .52 = 6L254 ' 14 l h fPath 1-1- is stronger than w1-1 so i ts is acceptable per UG-41 (b) (1)
toad for paEh 2-2 lesser of w or Vl2-2 = 7260.986 l -bfPa th 2 -2 rh ru (1 ) , (A ) = 25694 .62 + 29L03 .09 = 54797 ' 71 l b fPaEh 2-2 is stronger tharr w so i t is acceptable per Uc-41{b) (2).
Reinforcement Calculations For Nozz]-e ldAP
Limits of re inforc€ment UG-4O
Paral lel to the vessel waIl d = 7.795 lnNorma1 tso the vessel wa11 outside 2.5* (tn-Cn) + tse = .625Normal to the vessel wa1l inside 2.5* (tn-Clr-C) = .525 in
Deterrirrat ion of Cbord Lengrtsh
Thetsa1 = ArcCos ( (l,o + RrI) /Rm)= Arccos ( (23 .01 + 3 .75) /84 .3548)= 7 1 . 5 0 4 8 1
Ttretsa2 = Arccos ( (r,o - Rn) /Rm)= A r c c o s ( ( 2 3 . 0 r . - 3 . 7 5 ) , / 8 4 . 3 5 4 8 )= 76 .80215
d = 2*Rm*Sin( (Theta2 - Theta]-)/2)= 2 * 8 4 . 3 5 4 8 * S i n ( ( 7 6 . 8 0 2 ] - 5 - 7 t . 5 O 4 8 I ) / 2 )= 7 . 7 9 6 l r L
- 1 * 0 . 2 1 0 1 ) ) * 1 6 7 0 0
= 2 9 1 0 3 . 0 9 l b f
REvQDoc No. V49t-074
in
3 .L2 -1996
N4-2ND ROYI-RIGET
Nozzle required thicloess
t rn = P*Rn / (Sn*E - 0 .5 *P)= 8 3 . 0 6 7 4 6 * 3 . 7 5 / ( L 6 7 0 O * 1 - 0 . 5 * 8 3 . 0 6 7 4 6 1= 0 . 0 1 8 7 i n
Reorirled- thickness tr frm tre-37(a) {1)
! r = P * L * M / ( 2 * S * E - 0 . 2 * p )= 83 .05746*84 .25*L / (2 *L6700* ! - 0 . 2 *83 .06746)= 0 . 2 0 9 6 i n
Area reouired
Al lowabl-e stresses: Sn = 16700, Sv =
f r1 = l esse r o f 1o r Sn /Sv so f rL =1fr2 = l -esser of 1 or Sn/Sv so fr2 =1
A = d*91*P + 2*tn*t . r*F* (1 - f r1)= 7 . 7 9 6 * 0 . 2 0 9 6 * 1 - + 2 * 0 . 2 5 * 0 . 2 0 9 6 * 1 * ( 1= A .534 i r r ' 2
Area avai]-able
A1 = Iarger of the following
1 6 7 0 0 , p s i
= r .289 !n^ 2
d* (E1* t -F * t r ) - 2 * tn * (E l_ * t -F * t r ) * (1 - f r1 )7 . 7 9 6 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 6 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 5 ) * (! . 289 i n^z
2* ( t+ tn ) * (81* t -F * t r ) - 2 ' t t n * (E l_ *c -F* t r ) * (1 - f r1 )2 * ( 0 . 3 7 5 + 0 . 2 5 ) * { 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 6 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 *-2O7 i.']^2
= O .289 irl^ 2
0 . 2 0 9 5 ) * ( 1 - 1 )
A2 = smaller of the following
= 5* ( tn - t rn) * fT2*L= 5 * ( 0 . 2 5 - O . 0 L 8 7 ) r . 1 * 6 . 3 t U= .434 i .n^ 2
= 5* ( t .n - t rn) * f r2*tn= 5 * ( 0 . 2 5 - 0 . 0 1 8 7 ) * 1 * 6 . 2 5= .289 j .n^2
A41 = Leg^2 *frz= 0 . 2 5 ^ 2 * L = . 0 5 3 i n ^ 2
A r e a = A 1 + A 2 + A 4 1= L . 2 8 9 + 0 . 2 8 9 + 0 . 0 6 3= 1.64a i - t^ 2
As Area > A Che reinforcemenL is adequate
3 . t 2 . L 9 9 6
8 3 . 0 5 ? 4 5 a r
REVODoc No' V49l'074P.- ll. "{ 1*
for MAP = 70 Deg F
N4-2IID ROII-RIGIIT
Reinforcement check in the Blane para11el to the long. axis
Area required
A = d * t r *F + 2 * tn * t r *F* (1 - f r 1 )= 7 . 5 * 0 , 2 Q 9 5 * L + 2 * 0 . 2 5 * 0 - 2 0 9 6 * L * ( 1 _ 1 )= L -572 j .n^ 2
Area awailab]-e
A1 = larger of the following = L.24 in^2
= d* (E1* t -F* t r ) - 2*Ln* (E l * t -F* t r ) * (1 - f r1 )= 7 . 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 5 ) - 2 * 0 . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 0 9 6 | *= L .24 in^ 2
I ' � l - 1
- 1 * 0
0674
. 3 7 5
a ts -
= 2 * ( t + t n ) * ( 8 1 * t - F * t r ) _ 2 * t n * ( E 1 * t _ F * t r ) * ( 1 _ f 1 1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 _ l - * 0 . 2 0 9 6 ) _ 2 * 0 . 2 5 * ( 1 * 0= .2O7 j 'n^z
, 6 9 5 1 * ( 1 _ 1 )
A r e a = A 1 + A 2 + A 4 1= L . 2 4 + 0 . 2 8 9 + 0 . 0 5 3= ! . 5 9 2 l n 2
As Area > A the reinforcement is
check the we]-ds - Frm uw-16 (d) :
tmin = lesser of 0.75 or tn or t ,t l or C2 (min) = lesser of 0.25 ort 1 ( a c t u a l ) = 0 . 7 * L e g = O . 7 * O . 2 5 =t2 (ac tua l - ) = 0 .1875 in
Wall thickness per UG-45 (a) :waL l th ickness per UG-45(b) (1 ) :WalI thickness per IIG-16 (b) :Srd pipe wall per UG-45 (b) (4) :The greater of tr2 or tr3:Ttre lesser of tr4 or tr5:
adequate for MAP =
tmin = 0 .25 in0 .7* !min , t1 (min)0 . 1 7 5 i n
5 a t 7 0 D e g F
t ] - + E .2 = 0 .3625 >= 1 .25* tmin
Tlre weld sizes for t1 and E2 ar�e satisfaciory.
IIC9-45 llozzle Neck Thickness Check
= 0 . 1 7 5 i n
t r 1 = 0 . 0 1 8 7 i n ( ELr2 = 0 .2 0 95 ints r3 = 0 .0625 int r 4 = 0 . 2 8 1 7 5 i nr , r 5 = 0 . 2 0 9 5 i nt r 6 = 0 . 2 0 9 6 i n
Req'd per UG-45 is the larger of tr1 or tr6 = 0.2095 in
Available rLozzl-e wall thickness new, tn = 0.25 in
Ttre nozzle neck thickness is adequate for MAP.
a A1lowable stresses in j oint's UG-45(ct and UIY-15 (c)
REVODoc Ni. v49'l-{l?4
3 . 1 2 . 1 9 9 6
N4 -2I{D ROW_RIGIIT
Groove weld i -n tension = 0.74*L67O0 = 12358 psiNozz le wa l l i n shea r = o .7 *L67oo = 11690 ps iInner f i l let weld in shear = 0.49*15700 = 8183 psi
Strenqth of welded ioints:
(1) Inner f i l let weld in shear( P ! / 2 \ * N o z z l - e O . D . * L e g * S i = 1 . 5 7 * 8 * 0 . 2 5 * 8 1 8 3
(3) Nozzle walI in shear
= 2s594.62 IbE
3s5F9 . s2 lb f
( P i l 2 ) * N o z z L e o . D . * t w * S g = 1 . 5 7 * 8 * 0 . 1 8 7 5 * 1 2 3 5 8
Ladinq on welds Der lre-41 (t) (1)
W = (a - (d - 2 , ' t n ) * (BL*E - F * t r ) ) *Sv= 0 . 6 3 a - ( 7 - 7 9 5 - 2 * 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 - * 0 . 2 0 9 6 ) ) * 1 5 7 0 0= 7 L 3 4 . 9 3 4 l b f
W1-1 = (A2 + A5 + A41 + A42)*go'= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 ) * 1 5 7 0 0= 5 8 7 8 . 4 l b f
W 2 - 2 = ( A 2 + A 3 + A 4 1 + A 4 3 + 2 * t n * t * f r 1 ) * S v= ( 0 . 2 8 9 + 0 + 0 . 0 6 3 + 0 + 2 * 0 . 2 5 * 0 . 3 7 5 * 1 ) * 1 6 ? 0 0= 9 0 0 9 . 6 5 l b f
toad fo r paLh 1 -1 l esse r o f w o r W1-1 = 5878 .4 l b fPath 1-1 rh ru (1 ) a (3 ) = 25694.52 + 355s9.52 = 6L254.14 th fPath 1-1 is stronger than wL-1 so i t is acceptable per UG-pl(b) (1)
Load for paEh 2-2 lesser of w or w2-2 = 71'34.934 LbfPaL}r 2-2 thru (1) , (A) = 25694.62 + 29a03.O9 = 54797.7'J- LbfPaEtr 2-2 is stronger than w so it is acceptsable per rtc-4L (h) (2).
(Pirl21 *1'1..t y;,.ozzle dia. *tn*Sn =
(4) Groove weLd in tension
I . 5 7 * 7 . 7 5 * O . 2 5 * ] . � L 6 9 0 =
Reinforcement Calculations for Blctel:nal Pressure
Limits of re inf orcemept ue-40
Paral le1 to the vessel wal l d = 7.796 lnNonnal to the vessel wa1l outside 2.5* ( tn-Cn) +NormaL to the vessel wal1 inside 2.5t ( tn-Cn-C)
DeterRination of Chord Leng|th
TheEal = Arccos( (Lo + FJI),/Rm)= A r c c o s ( ( 2 3 . 0 1 + 3 . 7 5 ) , / 8 4 . 3 8 9 3 5 )= 71 .5L256
Thet.a2 = Arccos((Lo - Rn)/Rm)= A r c c o s ( ( 2 3 . 0 1 - 3 . 7 5 ) / 8 4 . 3 8 9 3 s )
3 -L2 -L996
= 2 9 1 0 3 . 0 9 l - b f
Ee = .625 i n= . 6 2 5 i n
4EvOIloc No. v4ql-074
II4 - zI[D ROYI-RIGITT
= / b . a t u / b b
d = 2*Rm*Sin( (Theta2 - Thetal) , /2)= 2 * 8 4 . 3 8 9 3 5 * S i n ( ( 7 6 . 8 0 7 6 6 - 1 1 . 5 L 2 6 6 ) / 2 )- ? " o 4 i t . t
Iilozzle recuired thickness
L / D o = 3 . O s 7 / 8 = . 3 8 2 1 D o / E = 8 / O . O I 9 6 L =From tab le G: A = 0 .000441From tab le I IA-3 : B = 4855.1
Pa= 4*B/ { 3 *Dolt )= 4 * 4 8 6 6 . A / B * e / 0 . 0 1 9 5 1 )= 1 5 . 9 0 4 p s i
Nozzle required thickness tsrn = .01951 in
Reouired tshicloess tr frm lre-37(d) (11 = .2787 in
Area required
A]. lowable st.resses: Sn = 747oQ, Sv = 14700, psi
f r1 = lesser o f 1or Sn/Sv so f r1 =1-fr2 = lesser of 1 or Sn/Sv so fr2 =1
A = 0 . 5 * ( d * t . r * F + 2 * t n * t r * F * ( 1 - f r ] . ) )= 0 . 5 * ( 7 . 7 9 6 r , 0 . 2 7 8 7 * ! + 2 * O . 2 5 * 0 . 2 7 8 7 * t * ( 1 - 1 ) )= 1 . 0 8 5 4 i n ^ 2
Area available
407 .955r -
A1 = larger of the following = .75L in^ 2
= d * (E l *C-F* t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 7 . 7 9 6 * ( 1 * 0 . 3 7 5 - t _ * 0 . 2 7 8 7 ) - 2 * O . 2 5 * ( 1 , * 0 . 3 7 5 - 1 * 0 . 2 7 8 7 ) * ( L - L )= .75r j-n^2
= 2 * ( t+ t ,n ) * (E1* t -F * t r ) - 2 * tn * (E l_ * t -F * t r ) * (1 - f r1 )= 2 * ( 0 . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 _ 1 * 0 . 2 7 8 7 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - L * 0 . 2 7 8 7 ) * ( ] - - t l= .t2 Ln^ 2
A2 = smaller of lhe following = 0 . 2 8 8 i n ^ 2
q* al-1.| - l - r"r I *f r?*l-
5 * ( 0 . 2 5 - 0 . 0 1 9 6 1 ) * 1 * 0 . 3 7 5.432 j-r:I^ 2
5* ( !n - t rn) * f12*gtt5 * ( 0 . 2 5 - 0 . 0 1 9 6 1 ) * 1 * 0 . 2 5.288 l rL^z
REVODoclNo. v49-l4743 . 1 2 . 1 9 9 5
A41 = Leg^2*fr2- 0 . 2 5 ^ 2 * 1 = . 0 6 3 i n ^ 2
A r e a = A l - + A 2 + A 4 1 -= 0 . 7 5 1 + 0 . 2 8 8 + 0 . 0 6 3= 1 . 1 0 2 i n ^ 2
As Area > A the reinforcement
N4-2IID ROW-RTGET
is adequaLe for Pe = L5.82647 at 400 Deg F
Area required
A = 0 . 5 * ( d * t r * F + 2 * t n * t r * F * ( 1 - f r 1 ) )= 0 . 5 * ( 7 . 5 * 0 . 2 7 8 7 * L + 2 * 0 . 2 5 * O . 2 7 8 7 * l * ( 1 - 1 ) )= L.045725 j-n^z
Area avaiLable
Al- = Larger of the following r - - . : - ^ .= . T Z Z J . L L 4
= d* (E1* t -F * t r ) - 2 * tn * (E1* t -F * t r ) * (1 - f r1 )= 7 . 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 7 8 7 ) - 2 ' , O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 7 I 7 ) * ( 1 r 1 )= .722 i rr^2
= 2 * ( t+ tn ) * (E1* t -F * t r ) - 2 * tn * (81* t . -F * t r ) * (1 - f r1 )= 2 * ( O . 3 7 5 + 0 . 2 5 ) * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 7 8 7 ) - 2 * O . 2 5 * ( 1 * 0 . 3 7 5 - 1 * 0 . 2 7 8 1 1 * 1 1 - a 1= .a2 in^ 2
A r e a = A 1 + 4 2 + A 4 1= O . 7 2 2 + 0 . 2 8 8 + 0 . 0 6 3= L .O73 in^ 2
As Area > A lhe reinforcement is adequate for ps = 15.82647 at. 400 Deg F
IIG-45 Nozzle Neck T'hickness Check
Wa lL th i ckness pe r UG-45(a ) : t r 1 = 0 .01951 in (E = 1 )WaI l t h i ckness pe r UG-45(b ) (2 ) : t r 2 = 0 .0454 i nv{a11 thickness per UG-16 (b) : tsr3 = 0.0625 inS td p ipe wa l l pe r UG-as (b ) (a ) : t r 4 = 0 .28175 inThe great.er of LT2 or t . r3: t r5 = 0.0625 inThe lesser of t r4 or Er5: t r6 = O.0625 in
Req'd per UG-45 is the larger of Er1 or t r6 = 0.0625 in
Available yjozzl-e wa1l Ehickness new, tn = 0.25 in
The nozzle neck thickness is adecnrate for Pe.
Rf,VODoc Nd. V{91-0743 -L2 -L996
ENGINEERINGCALCULATIONS
DE.SIG'}*J Otr I]AM N62-?LE.JAcklrdc- Bo(r AsSEi/rBuE5
PROJECT: I \r-n \ l^.' --U;LM E .:):J1?Mg.tJ* PROJECT NO: \ ra<r\ na r t / \ t - y '
9ee- (aaD-, c>t: i:A,.-d'J -A1,3nj
i
CAI,CULATIOn*S: (SEE ATTACIIED)
VO+9 -t -o48pAae- Z -e l4
1.0 oBJECTII/E
Thf obincliw of this calculglion is lo ptffarn the slruetutgl dtsign and Endtysis fOr lheJacking Eoll Assemhlies on the HorizgrilBlArcess liodule Chsrnber (HAltl] b?ilq,esno?zle.
2.0 TdETI|OD OF AIALYSIS / COHPUTER PROGRAil$ & UERSIOX
No computer pro$Ems er€ used in the exect.dion df this calcu|atien:
Jacking Bolls ar€ placed in localions thal ryill permit operalion without inlerfereneps w[holher components. The overall desigin musl nol permil arry of lhe components {o exlendover lhe flangE fEce because of lestrictions in the removal ofthe adjacenl adader.
The Jscking Bolt Assembly components are designed lo AISC allo$'able ElresseF and bynranual design methods for lhe grealer of lwo condilions:
r Installalion and eqdpm€nt selicing dudng which time bellows spring iorces +el but nopressure loads e*sl.
r FnM Vessel ftee standing full vacuutn gressure test wilh bellur,/s pressule loads €ctinEon lhe lscldng assamblles.
Wrlds arc 3i2cd by lra{itional manual calculalions found In st8ndald tnginttrlng lc)G3.
3.0 GFXEFAL A$SUHmorS
None resririnE confirmdion
il.O REFEREICES
1. ASME Boiler snd PrEssute Vessel Code, Seclion \Jll|, Division l, 1995 Edfilon
2, Roark & Young, Formulas for $lress gnd Slrain, Fifrh Edltlon
3. Blodgelt, Dasign of fVelded Siructufe5
4. LIGG Vacuum Equipmed Slruclural Design Crflcria , Po -. l) o .
5. AlSc Stecl Construcllon l\/laflu8l
6.8 COtCLUS|OTS
The Jacking Bolt ori6ntEtion eround the l'lAfr/l nozde Bfld the asserflbly cotnponeii delailsere f0und in lhe body ofthis cslculaliDn.
The localiofl of the "D" noEte {electricslllnslr. fsedlhroughs, ultlity) located on lhe vedicalEenterlinG of the l-lAM vessel mey requke relocation due lo posFible iflterf€r€ncc with lhejacking bolts andror ils close proximity to the '8" no'ale jundure ( 6pprox. l')
{ a v 9 - t - e 6 <
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o o o
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+Z Fr + F'v= 154no
2Fr*.? + 4t Fz= o
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7\-- G4Xo+
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: + q2,5 xrS = 4mn'+2 ? o r o
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rM..I
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l l + a it ua'?A /+
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tt-
fz-z 14 8? I
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tle-r.ll 9"2€ = t? 3oo+.)
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= Z2.b t lsl 17)l l *rt-'r-
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(l"ue.e- E*€Ar)
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. ? - \
t- - .-- :r c - A
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t? . aoo - r r i , .1 -
f l+D 5 = 1"3?3"
1 5 / , r + 7 / 4 - 1 " : 1 ? r u 'I x /-.93?S
= ?3,o* J7
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rz.3'<rt(,838JT
* q6o,= .44
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o c 0
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fu'r- t - ug)L..........-.. -= -
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f,v rn'-
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}rs *-* Fo(L
Yg'corcscu e'^'t
'/"'S e-o
Vo+g -tro+ IP,+6-e B oF
flename: FULLCIR.wRIUtT CIRCUTAR/TRUHNION FItI-ET WELD
8€twpEn Dart and part a-E-vi,3
r"Tff"ii,iH.* ^ lrt
A DI1I
2.833 0.552
l-2-
i<f t' a| / - ' . - / ' , - \
h{l lvl?0.00 u.Bo 0.00
-)
)t-.J
GE0l"€]RlC Dt#NSlOltls tFOR FI.AT PIATES, IHPUT D=100'd)drt, Dp
0.8s8 1000.000
SECTIOITI PROPERTIESJy{ rAtELO STFESS {PSl)
1.103 'ts008
EFFECTII,E T}IROAT CORRECTIO},I FACTORIvlf
t .00
l\4Axlid.fvl t\tELD LOAD {f.l - #lllcH4672
REQUTREO FILLET WELD S|ZE (tt{CHES}
0.367 L\>e =z! F .:-e- ','iF-D
filename: FULLRECT.WRIAtI. AROUND RECTASIGULqR OR SQUARE FILLET'I^'ELD
Between pan FLAN{:IE LIJA and part Ft-cr'r6-=
*. " l t
M118451.00
7.S39
t'ta ,P-f.y-
/ -t-
vrvr,C.Fr
Fn-
LOAD |NPUT { LBS., NeH{8S. }F1 F2 F3
0.00 12308.00 0.00
GEOhIETRIC Dh,EHSIONS
0.90 0.00
SKEIIJED A'{BLE{90"}g< I 20' }$8.000
M3TT2
a b WELD STRESS {PSI}3.000 0.625 18000
SECTIOI{ PROPERTIESA Swl fur3
2.005?.250 4.875
EFFECTIVE THROAT CORRECTION FACTORnrf
1.00
rvrAx$,[.srwEto roAD tf] -#rNcH
5,181
REOUIRED FILTET I-JELD SEE 'I!{CHES}W
0.tl31
e1{.500
c30.313
U:e I Fru ler WELD
vo49-r-043PA6e 9 cF t4
lilrname: CHHL-V'ILD.IVR IEI{ANI{EL.SIUPED F ILLEI WELDS
I{OTE: FOR AIL A,ROUI{D lrlEtD USE {f}/2 TO SIZE WELD LEG
Bcrr{cen padiiAg--UD=.:E--anu part No?urg ERAc<E:f
+
---t-
FzI.OAD INPUT { LBS,, IHCH+BS.
Fl F212300.00 0.00
lf3 Ml
0.00 0.00fri2 M3
0.00 4t513.00
SKEWED Ar{GLE(90">B<1 35"}s0-000
6EO|!€1Rle DE\iEHSlOllSa b WELB STRESS6,000 4.000 18800
SECTION PROPERTIESAtit.00G
Cp2.857
Swt30.000
ts2'[.381
.i114.381 3.000
c3| . l t tg
EFFECT|\JE THROAT CORRECTIOfi FACTORh4f
1 .00
hit$$r{..h4WELD LOAD {B -{FINCHf
49t,1
.€OUHIED FILLET WELD SIZE {IHCHES}t {
0.388
Use L. PruLF-ru)
1/16 rvvr:
r F-3
.ao
(3 srpas)
- \ o4C- \ - s43FAee lC oF l+
A1u Aaao*to
odisrPF- 806€-5
COMPRESS 4.20 ham
V o49 -[-o4s.PA6E II OF
UIFr - 27 ,\4t996
No??ug =Her-t- ETfLESS DuLlr.lG FUL\-bracket WRC bulletin l-07 design
lfi;;;-re€i
ASME code Addenda used - A90Internal design pressureDesign tenperature isCorrosion aLlowanceShell inner diameter, newshel l th ickness, nerr tIrfat' I is exempt from inpactAl-IovJable tensile stressLug length. circ directionLug length, long direct ionLug interface radius
P :-15 psi: 7 O d e 9 F
C : 0 i n .D i : 6 0 . 5 i n .t = . 5 i n .
testinq per UHA-51- ( a )S : L 8 8 0 0 p s i f o r s A
2C1 : 6 i n .2C2 = 4 in.
: . 5 i n .
240 304 HIGH A88^
Applied Loads
Radial ]oadCircurnferential rnomentLongitudinal momentCircumferentiaf shearLongitudinal shear
Stresses at the lug interf ace per lilRc
Geometric factor garnma = 61Stress concentration factor KnStress concentration factor KbBetal- : 9.a360668-o2, Beta2 =
P r =M c =
V c =
0 lbf0 I b - i n41-513 lb- in0 lbfl -2300 lbf
bu l l e t i n 107
( tens ion) = 1(bending; : 1
9 . 8 3 6 0 6 6 E - 0 2
Circumferential (hoop) stress psiFrom! r g .
VaIueread
betaD1CuBIA1Au Bu Du
pressure stress*4C*3C*
1C3A*1A3B*t-B
LO .2168 . 5 8 6. 0 7 5. l -o92 . L 4 8. o96 . 8 5 8. o 4 2
. 0 9 8
. 0 9 8
. 0 9 8
. 0 9 8
. 0 9 8
. 1 - 0 9
. 0 9 8
. 0 9 8
-9080
o
- 9 0 80
0
-9080
0
-908o
o
- 9 0 I
o
-908 -908 -908
0 0 0
00o
U
0o
o00
-5559 -5559- l _ 4 0 0 0 1 4 0 0 0
5 5 5 9 5 5 5 9t - 4 0 0 0 - 1 4 0 0 0
Total hoop stress -20467 7533 18651- -9349 -908 -908 -908 -908
Primary mem.branecirc. stress*
-6467 -6467 465L 45 51 - 9 0 8 - 9 0 8 - 9 0 8 -908
l,taximum prirnary mem.brane circ. stress =-6467 PsiAlloerable prinary nembrane circ. stress : +-1-5*S = +- 282oo ps i
v o49- l - sA8PlsE l2cP l{
4 . 2 0
- 2 -
hanCOMPRESSr ;;"naximurn primary rnenbrane circ. stress
Longitudinal (axial) stress psiFronF i s .
Valueread Au B} D1
Dressure stress* -454 -454 -454 -454 -454
0
- 4540
-454 -4540 04Ctl
3C*t-c-l-2C4A*2A4B*Z E
L 0 . 2 L 68 , 5 8 6. t- 11,. 0 7 43 . 2 3 4. o472 . O 7 4. o62
. 0 9 8
. 0 9 8
. 0 9 8
. 0 9 8
. 0 9 8
. 1 1 1
. 0 9 8, 1 0 5
0o0
00
0
00
o0o
o0o
000
-1797 -L797- 1 9 2 8 8 1 9 2 8 8
17 97 J -7 97r92AA -L9288
Total Axial stress -2L539 !7037 2063r -L7945 -454 -454 -454 -454
Prinary rnembranelong. stress*
-2251 -225L L 3 4 3 1 3 4 3 -454 -454 -454 -454
Maxiroum prirnary menbrane long, stress :-2251- psiAIIowabIe prinary membrane long. stress = +-1 .5*S =
The naximun prirnary membrane long. stress is within
+- 28200 ps i
alloh/able li-rnits
Shear stress psiLoading
cu CI Du D1
torsion moment }ltcirc. load vcLong. foad Vc
00
Total Shear stress
-2050 -2050 2050 2050
o -2050 -2050 2050 2050
COMPRESS4 . 2 0
- 3 -
ham
Vo49- l -o48FAoe /3 op 14
-I1L-31:-1331o-At point -->
Combined stress intensity, psi
Au AI Bu B1 cu C] Du D1
Combined stress -21539 L?O37 2063L -L7945 4125 4J.25 4]-25 4125
Maxinum combined stress =-21539 psiAl1oi,rab1e combined stress : *-3*S = +- 56400 psi
The ruaximun cornbined stress is within al-lohtabLe linits.
voAg-l-o48PAe]e \4 sF 14
frer-econ ER TRANsM rrrAl
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Te€pipre t619)421.1$s
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