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TECHNICAL PAPERS: Gas Turbines: Cycle Innovations

Component Map Generation of a Gas Turbine Using Genetic Algorithms

[+] Author and Article Information
Changduk Kong

Department of Aerospace Engineering,  Chosun University, #375 Seosuk-dong, Dong-gu, Gwangju 501-759, Koreacdgong@mail.chosun.ac.kr

Seonghee Kho

Department of Aerospace Engineering,  Chosun University, #375 Seosuk-dong, Dong-gu, Gwangju 501-759, Koreahabari@paran.com

Jayoung Ki

Department of Aerospace Engineering,  Chosun University, #375 Seosuk-dong, Dong-gu, Gwangju 501-759, Koreasetgods@hotmail.com

J. Eng. Gas Turbines Power 128(1), 92-96 (Mar 01, 2004) (5 pages) doi:10.1115/1.2032431 History: Received October 01, 2003; Revised March 01, 2004

In order to estimate the precise performance of the existing gas turbine engine, the component maps with more realistic performance characteristics are needed. Because the component maps are the engine manufacturer’s propriety obtained from very expensive experimental tests, they are not provided to the customers, generally. Therefore, because the engineers, who are working the performance simulation, have been mostly relying on component maps scaled from the similar existing maps, the accuracy of the performance analysis using the scaled maps may be relatively lower than that using the real component maps. Therefore, a component map generation method using experimental data and the genetic algorithms are newly proposed in this study. The engine test unit to be used for map generation has a free power turbine type small turboshaft engine. In order to generate the performance map for compressor of this engine, after obtaining engine performance data through experimental tests, and then the third order equations, which have relationships with the mass flow function, the pressure ratio, and the isentropic efficiency as to the engine rotational speed, were derived by using the genetic algorithms. A steady-state performance analysis was performed with the generated maps of the compressor by the commercial gas turbine performance analysis program GASTURB (Kurzke, 2001). In order to verify the proposed scheme, the experimental data for verification were compared with performance analysis results using traditional scaled component maps and performance analysis results using a generated compressor map by genetic algorithms (GAs). In comparison, it was found that the analysis results using the generated map by GAs were well agreed with experimental data. Therefore, it was confirmed that the component maps can be generated from the experimental data by using GAs and it may be considered that the more realistic component maps can be obtained if more various conditions and accurate sensors would be used.

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Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 1

Thermodynamic schematic diagram of the small turboshaft engine

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Figure 2

Flow chart of genetic algorithm

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Figure 3

Converge of object function as generation

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Figure 4

Compressor map generated by GAs

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Figure 5

Power, fuel flow, SFC, and air flow as to RPM

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