Adaptation Method for Overall and Local Performances of Gas Turbine Engine Model

Original Paper

Abstract

An adaptation method was proposed to improve the modeling accuracy of overall and local performances of gas turbine engine. The adaptation method was divided into two steps. First, the overall performance parameters such as engine thrust, thermal efficiency, and pressure ratio were adapted by calibrating compressor maps, and second, the local performance parameters such as temperature of component intersection and shaft speed were adjusted by additional adaptation factors. An optimization technique was used to find the correlation equation of adaptation factors for compressor performance maps. The multi-island genetic algorithm (MIGA) was employed in the present optimization. The correlations of local adaptation factors were generated based on the difference between the first adapted engine model and performance test data. The proposed adaptation method applied to a low-bypass ratio turbofan engine of 12,000 lb thrust. The gas turbine engine model was generated and validated based on the performance test data in the sea-level static condition. In flight condition at 20,000 ft and 0.9 Mach number, the result of adapted engine model showed improved prediction in engine thrust (overall performance parameter) by reducing the difference from 14.5 to 3.3%. Moreover, there was further improvement in the comparison of low-pressure turbine exit temperature (local performance parameter) as the difference is reduced from 3.2 to 0.4%.

Keywords

Performance adaptation Gas turbine Engine model Adaptation factor 

Nomenclature

AF

Adaptation factor

eff

Efficiency

HPC

High-pressure compressor

HPT

High-pressure turbine

LPT

Low-pressure turbine

MIGA

Multi-island genetic algorithm

Nc

Corrected rotation speed

PR

Total pressure ratio

SFC

Specific fuel consumption

T03

High-pressure compressor exit total temperature

T05

Low-pressure turbine exit total temperature

T09

Engine nozzle exit total temperature

Wc

Corrected mass flow rate

XN2

Low spool speed

Station number

0

Engine inlet

1

Fan inlet

2

Splitter inlet

21

Inlet of duct in front of HPC for core side

25

HPC inlet

31

Combustor inlet

4

HPT inlet

44

Inlet of duct in front of LPT

45

LPT inlet

5

Inlet of duct in front of mixer

6

Mixer inlet

7

Nozzle inlet

9

Nozzle outlet

16

Outlet of bypass duct

Notes

Acknowledgements

This work was supported by a 2-Year Research Grant of Pusan National University

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Copyright information

© The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  1. 1.Department of Aerospace EngineeringPusan National UniversityBusanRepublic of Korea
  2. 2.School of Mechanical EngineeringPusan National UniversityBusanRepublic of Korea

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