SHORT AND LONG RANGE MISSION ANALYSIS FOR A GEARED TURBOFAN WITH ACTIVE CORE TECHNOLOGIES

Short and Long Range Mission Analysis for a Geared Turbofan with Active Core Technologies

A. Alexiou, N. Aretakis, I. Roumeliotis, K. Mathioudakis 1

Laboratory of Thermal Turbomachines

National Technical University of Athens

Short and Long Range Mission Analysis for a

Geared Turbofan with Active Core

Technologies

A. Alexiou, N. Aretakis, I. Roumeliotis, K. Mathioudakis



INTRODUCTION

METHODOLOGY

o Engine Performance

o Aircraft Performance

o NOx Emissions

o Noise

RESULTS


o Aircraft Performance & NOx Emissions

o Noise

o Sensitivity Analysis

SUMMARY & CONCLUSIONS

Contents



ACARE Targets for Year 2020

The engine contribution towards ACARE goals are:

80% NOx emissions reduction relative to CAEP/2 ICAO

LTO cycle limits

20% reduction in fuel consumption (and hence CO2

emissions) per passenger-kilometre

10 dB noise reduction per certification point compared to

a year 2000 in service engine (e.g. CFM56, Trent 700).



Geared Turbofan with Active Core Technologies

(GTAC)

A c tiv e C o o lin g

A ir C o o lin g

G e a rb o x

A c t iv e

S u rg e

C o n tro l

A c t iv e C le a ra n c e

C o n tro l

F a nL P C

L P TH P C

H P T

C C H

High BPR → High Propulsive Efficiency, Low Jet Noise

Gear → optimum speed for LP components in terms of

efficiency, stage loading, stage count and noise

PERM or LDI combustor → low NOx formation



Geared Turbofan with Active Core Technologies

(GTAC)

A c tiv e C o o lin g

A ir C o o lin g

G e a rb o x

A c t iv e

S u rg e

C o n tro l

A c t iv e C le a ra n c e

C o n tro l

F a nL P C

L P TH P C

H P T

C C H

Active Systems

→ engine adjusted for optimum performance and/or safety

at component or engine level according to its actual

operating conditions or component/engine health status

→ increases flexibility during the design phase since it is no

longer required to base the design on a worst case scenario.



Paper Objectives

Develop an integrated approach by coupling together

different simulation codes in order to determine the fuel

consumption, noise and NOx emissions of any aircraft-

engine combination and aircraft mission

Implement this approach for:

a short range mission (1000 km) using a 140 kN T/O

SLS thrust version of the GTAC engine

a long range mission (5500 km) using a 325 kN T/O

SLS thrust version of the GTAC engine

Compare the results with corresponding ones for

year-2000 in service engines of similar thrust ratings

(baseline engines).



INTRODUCTION

METHODOLOGY



o NOx Emissions

o Noise

RESULTS



o Noise



Contents



Module Interaction Diagram



Engine Performance (PROOSIS)

PROOSIS

Simulation

Environment

PROOSIS

generated

executable

deck



Aircraft Performance (CAMACM)

CAMACM

Graphical User

Interface



NOx Emissions (CAMACM)

5.0

GTAC,3BASE,3

GTAC,3GTAC,3

GTAC,3BASE,xGTAC,x)T(P

)T(P)T(EINOEINO

345

1471T8.137.0

3

4x

3

e267985.30

PT0075492.0EINO

Eq. 1

36.0

3

68.0

3

32.1185

3T

x%PPPFARe104.0EINO

NOx emissions calculated using the Boeing Fuel Flow Method 2

Since there are no ICAO data for GTAC engines then:

Approach 1: Assume same combustor technology as

Baseline engines and a modified P3T3 method:

Approach 2: Use publicly available correlations for new

technology combustors such as:

or

Eq. 2

Eq. 3



Noise (AERONOISE)

Engine

Performance &

Geometry Data



INTRODUCTION

METHODOLOGY



o NOx Emissions

o Noise

RESULTS



o Noise



Contents



PARAMETER BASESR BASELR

Altitude (m) 10668 11500

Mach Number 0.78 0.82

FN (kN) 21.0 47.4

SFC (gr/kN∙s) 17.5 17.0

W1 (kg/s) 134 306

BPR 5.2 5.2

OPR 26.6 32.4

P A R A M E T E R B A S E S R B A S E L R

B P R 5 5

O P R 2 9 3 6

W 1 (k g /s ) 3 6 0 9 2 0

F N (k N ) 1 2 0 3 1 5

S F C (g r /k N ?s ) 1 0 .4 1 0 .1

Baseline Engines Performance

Main Cycle Parameters

for Baseline Engines

at T/O SLS

Predicted Main Cycle Parameters

for Baseline Engines

at Mid-Cruise (ISA, installed)



8

10

12

14

0 20 40 60 80 100

% max Thrust SLS

SF

C (

gr/

(kN

.s))

BASESR Engine Model

BASELR Engine Model

SFC-FN variation of Baseline Engines at SLS



FAN

LPC

HPC HPT

LPT

CCH

HEX

GBX

ATM

INL

NBP

NCO

DLP

DHP

DBP DHX

D30

RBP

HPS

LPS

D51

FAN

LPC

HPC HPT

LPT

CCH

HEX

GBX

ATM

INL

NBP

NCO

DLP

DHP

DBP DHX

D30

RBP

HPS

LPS

D51

GTAC Performance Model & Data



-2.0 -1.5 -1.0 -0.5 0.0 0.5 1.0 1.5 2.0

% Difference from Specifications

FN

SFC

OPR

W31

Take-off

Top-of-Climb

Mid-Cruise

ICAO SLS 100% FN

ICAO SLS 85% FN

ICAO SLS 30% FN

ICAO SLS 7% FN

Comparison of Model Predictions and NEWAC

Specifications for GTACSR



Aircraft Performance

Aircraft Characteristics

Main Mission Parameters



Overall Mission Results for Baseline Engines



Comparison of GTAC with BASE Engines



Variation of SFC and NOx with Mission Time for LR



LTO Cycle NOx Emissions

Short

Range

Long

Range



ICAO-LTO Cycle NOx Emissions Predictions



Noise Results

Effect of -1 EPNdB per source on total noise

Short Range Long Range



Fuel Burn and NOx Variation for 1% Increase of

Selected Core Design Parameters



INTRODUCTION

METHODOLOGY



o NOx Emissions

o Noise

RESULTS



o Noise

o Weight



Contents



Summary & Conclusions (I)

An integrated approach is used to assess the potential benefits of the

GTAC concept in terms of fuel burned, NOx emissions generated and

noise produced, over equivalent thrust engines of Year 2000 technology

during typical short and long range aircraft missions.

According to the performance expected by the manufacturer for this

engine, the modelling methods used and the assumptions made the

following conclusions are drawn:

The GTAC engines burn ~25% less fuel than their corresponding

baseline engines for the same mission.

For the same combustor design, the GTAC engines produce more

NOx emissions during the whole mission. For the LTO cycle, the LR

version of the engine generates less NOx compared to its baseline.

The corresponding Dp/Foo values are lower than those of the baseline

ones.



Summary & Conclusions (II)

Assuming new technology combustor designs, significant

reductions in NOx are achieved at mission and LTO cycle as

well as Dp/Foo values.

The combination of high BPR, low fan speed and fan pressure

ratio and smaller core of GTAC engines result in noise

reduction at all three noise certification points.

From the above, it appears that the GTAC concept has the

potential to meet current targets for reducing fuel consumption,

NOx emissions and community noise.

A sensitivity analysis has shown that even further improvements

are possible by optimising the most influential engine design

parameters.

SHORT AND LONG RANGE MISSION ANALYSIS FOR A GEARED TURBOFAN WITH ACTIVE CORE TECHNOLOGIES

Documents

Transcript of SHORT AND LONG RANGE MISSION ANALYSIS FOR A GEARED TURBOFAN WITH ACTIVE CORE TECHNOLOGIES