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Design and Development of a Nine Stage Axial Flow Compressor for Industrial Gas Turbines PUBLIC ACCESS

[+] Author Affiliations
G. D. Stringham, B. N. Cassem, T. C. Prince, P. F. Yeung

Solar Turbines, Inc., San Diego, CA

Paper No. 98-GT-140, pp. V001T01A042; 7 pages
doi:10.1115/98-GT-140
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 1: Turbomachinery
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7862-0
  • Copyright © 1998 by ASME

abstract

A nine stage industrial axial flow compressor with a pressure ratio of 9.1:1 was designed, built and rig tested. The modern technology and design tools developed by government/aircraft engine compressor technologists were used for an industrial gas turbine application. The compressor was designed with “arbitrary” airfoil blading including CFD analysis in all blade rows. Flowpath contouring in the hub region of the rotors was used to decrease losses. The compressor rig was tested at the Compressor Research Facility at Wright Patterson Air Force Base in Dayton, Ohio. Extensive testing included determining the impact of stator leading edge instrumentation on performance. The compressor demonstrated excellent efficiency and stall margin in its first build. This paper describes the aerodynamic design, test instrumentation and test results.

Copyright © 1998 by ASME
This article is only available in the PDF format.

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