Design and Testing of a Controlled Diffusion Airfoil Cascade for Industrial Axial Flow Compressor Application PUBLIC ACCESS

[+] Author Affiliations
W. Steinert, H. Starken

Institut für Antriebstechnik, Linder Höhe, Köln, W.-Germany

B. Eisenberg

MAN Gutehoffnungshütte AG, Oberhausen, Oberhausen, W.-Germany

Paper No. 90-GT-140, pp. V001T01A044; 9 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


Similarly as in jet engine development, modern design methods are used today to improve the performance of industrial compressors. In order to verify the loading limits, a cascade profile representative for the first rotor hub section of an industrial compressor has been designed by optimizing the suction surface velocity distribution using a direct boundary layer calculation method. The blade shape was computed with an inverse full potential code and the resulting cascade was tested in a cascade windtunnel. The experimental results confirmed the design intent and resulted in a low loss coefficient of 1.8% at design condition and an incidence range of nearly 12° (4% loss level) at an inlet Mach number of 0.62.

Copyright © 1990 by ASME
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