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TECHNICAL PAPERS: Gas Turbines: Cycle Innovations

A New Scaling Method for Component Maps of Gas Turbine Using System Identification

[+] Author and Article Information
C. Kong, J. Ki, M. Kang

Department of Aerospace Engineering, Chosun University, #375 Seosuk-dong, Dong-gu, Kwangju 501-759, Korea

J. Eng. Gas Turbines Power 125(4), 979-985 (Nov 18, 2003) (7 pages) doi:10.1115/1.1610014 History: Received December 01, 2001; Revised March 01, 2002; Online November 18, 2003
Copyright © 2003 by ASME
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References

Cohen, H., Rogers, G. F. C., and Saravanamuttoo, H. I. H., 1996, Gas Turbine Theory, 4th Ed., Longman, London.
Sellers, J. F., and Daniele, C. J., 1975, “DYNGEN-A Program for Calculating Steady-State and Transient Performance of Turbojet and Turbofan Engines,” NASA-TN D-7901.
Kong, C. D., and Ki, J. Y., 2001, “Performance Simulation of Turboprop Engine for Basic Trainer,” ASME Paper No. 01-GT-391.
Kong, C. D., 2000, “Propulsion System Integration of Turboprop Aircraft for Basic Trainer,” ASME Paper No. 00-GT-10.
Na, J. J., 1996, “A Study on PT6A-62 Engine Install Performance Analysis,” Agency of Defense Development, Technical Report.
Kurzke, K., 1999, GASTURB 8.0 Manual.
Douglas, I. E., 1986, “Development of a Generalized Computer Program for Gas Turbine Performance Simulation,” Ph.D. thesis, Cranfield University, Cranfield, UK.
Kong,  C. D., and Chung,  S. C., 1999, “Real Time Linear Simulation and Control for Small Aircraft Turbojet Engine,” KSME Int. J.,13, pp. 656–666.
Palmer,  J. R., and Yan,  C.-Z., 1985, “TURBOTRANS—A Programming Language for the Performance Simulation of Arbitrary Gas Turbine Engines With Arbitrary Control Systems,” Int. J. Turbo Jet Engines,2, pp. 19–28.
Schobeiri,  M. T., Attia,  M., and Lippke,  C., 1994, “GETRAN: A Generic, Modularly, Structured Computer Code for Simulation of Dynamic Behavior of Aero-and Power Generation Gas Turbine Engines,” ASME J. Eng. Gas Turbines Power, 116, pp. 483–494.
Seldner, K. et al., 1972, “Generalized Simulation Technique for Turbojet Engine System Analysis,” NASA-TN-D-6610.

Figures

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Station number and layout of the study engine
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Comparison between component maps obtained by the newly proposed scaling method (solid curves) and component maps obtained by the traditional scaling method (dotted curves)
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Flow chart of steady state performance calculation program
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Results of uninstall performance analysis with altitude variation (flight Mach No.=0)
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Results of installed performance analysis at ECS off condition (flight Mach No.=0.27, 0.38, and 0.48, altitude=0 m)
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Results of installed performance analysis at ECS maximum condition (flight Mach No.=0.27, 0.38, and 0.48, altitude=0 m)

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