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Vortex Control Over End Wall Flow in Compressor Cascades FREE

[+] Author Affiliations
Yan-Ping Tang, Mao-Zhang Chen

Beijing University of Aeronautics and Astronautics

Paper No. 90-GT-228, pp. V001T01A075; 8 pages
doi:10.1115/90-GT-228
From:
  • 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

abstract

Three methods of vortex control over the end wall flow in compressor cascades have been investigated experimentally. The total pressure loss at the exit of a linear compressor cascade is reduced 6.5%, 10.5% and 26.5% respectively by these methods for different incidences over a range of moderate-high values. The physics of these methods has been discussed and some new concepts of vortex control techniques in compressor cascades have been proposed.

Copyright © 1990 by ASME
This article is only available in the PDF format.

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