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

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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%.

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Abbreviations

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

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

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Acknowledgements

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

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Authors and Affiliations

  1. Department of Aerospace Engineering, Pusan National University, Busan, 46241, Republic of Korea

    Sangjo Kim & Kuisoon Kim

  2. School of Mechanical Engineering, Pusan National University, Busan, 46241, Republic of Korea

    Changmin Son

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  1. Sangjo Kim
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  2. Kuisoon Kim
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Correspondence to Changmin Son.

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Kim, S., Kim, K. & Son, C. Adaptation Method for Overall and Local Performances of Gas Turbine Engine Model. JASS 19, 250–261 (2018). https://doi.org/10.1007/s42405-018-0016-4

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  • DOI: https://doi.org/10.1007/s42405-018-0016-4

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