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Turbofan engine performance optimization based on aircraft cruise thrust level

  • Valdi Freire da Fonseca FilhoEmail author
  • Raphael Felipe Gama Ribeiro
  • Pedro Teixeira Lacava
Technical Paper
  • 22 Downloads

Abstract

The aim of this paper is to define a methodology to minimize the adjustment effort required to comply with aircraft design performance requirements, when commercial off-the-shelf turbofan engines are installed, which is a challenge to aircraft manufactures. In order to achieve an efficient operation, a reasonable proposal is to adapt the propulsive performance by turbofan engine optimization. This work is carried out according to the following steps: (i) creation of estimated performance curves for a gas turbine from limited data; (ii) analysis of the impacts on performance and propulsive integration, applying computer simulation of the most promising engine components configuration; and (iii) matching between the lowest specific fuel consumption and the net thrust required for the cruise flight phase of the aircraft. The technical feasibility and the possible predisposition of engine manufactures to perform the implementation were also considered as critical points in this procedure. As a final result, an evaluation that presents the most suitable turbofan engine component modifications proposal to comply with engine/aircraft performance integration to be applied in the conceptual design phase was obtained.

Keywords

Turbofan Aircraft engine performance Performance optimization Aircraft propulsion 

List of symbols

AR

Aspect ratio

BPR

Bypass ratio

CD

Aircraft total drag coefficient

CD0

Zero lift drag coefficient, without engine nacelles effect

CDi

Induced drag coefficient

CDw

Wave drag coefficient

CDexc

Excrescence drag coefficient

CDeng

Engine-related drag coefficient

Cf

Skin friction coefficient

CL

Aircraft lift coefficient

CMC

Ceramic matrix composites

DMC

Direct maintenance cost

ECS

Environmental control system

EIS

Entry into service

Eff_i

Efficiency of component i

e

Oswald factor

FNreq

Net thrust required

FPR

Fan pressure ratio

HPC

High-pressure compressor

HPT

High-pressure turbine

IDG

Integrated drive generator

IFPR

Inner fan pressure ratio

IPC

Intermediate-pressure compressor

IPCR

Intermediate-pressure compressor ratio

ISA

International Standard Atmosphere

KA

Airfoil technology factor

LPT

Low-pressure turbine

M

Mach number

Mcrit

Critical Mach number

MDD

Drag divergence Mach number

N/sqrt(T)

Corrected speed

NGV

Nozzle guide vane

OFPR

Outer fan pressure ratio

OPR

Overall pressure ratio

Seq

Aircraft equivalent parasite area

Sw

Wing reference area

SFC

Specific fuel consumption

\(\left( {\frac{t}{c}} \right)\)

Wing airfoil relative thickness

TET

Turbine entry temperature

TOC

Top of climb

W2

Maximum engine inlet mass flow at sea-level standard S ISA conditions

WCHN/W25

Turbine NGV cooling air flow ratio

WCHR/W25

Turbine rotor blade cooling air flow ratio

\(\varLambda_{c/4}\)

Wing quarter chord sweep angle

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Copyright information

© The Brazilian Society of Mechanical Sciences and Engineering 2019

Authors and Affiliations

  1. 1.Embraer S.A.São José dos CamposBrazil
  2. 2.Propulsion DepartmentInstituto Tecnológico de AeronáuticaSão José dos CamposBrazil

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