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Stall Inception in Axial Compressors PUBLIC ACCESS

[+] Author Affiliations
N. M. McDougall, N. A. Cumpsty, T. P. Hynes

University of Cambridge

Paper No. 89-GT-63, pp. V001T01A034; 10 pages
doi:10.1115/89-GT-63
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME

abstract

Detailed measurements have been made of the transient stalling process in an axial compressor stage. The stage is of high hub-casing ratio and stall is initiated in the rotor. If the rotor tip clearance is small stall inception occurs at the hub, but at clearances typical for a multistage compressor the inception is at the tip. The crucial quantity in both cases is the blockage caused by the endwall boundary layer. Prior to stall disturbances rotate around the inlet flow in sympathy with rotating variations in the endwall blockage; these can persist for some time prior to stall, rising and falling in amplitude before the final increase which occurs as the compressor stalls.

Copyright © 1989 by ASME
This article is only available in the PDF format.

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