Flow Measurements in Rotating Stall in a Gas Turbine Engine Compressor PUBLIC ACCESS

[+] Author Affiliations
R. C. Best, J. G. C. LaFlamme, W. C. Moffatt

Royal Military College of Canada, Kingston, ON, Canada

Paper No. 88-GT-219, pp. V001T01A078; 7 pages
  • ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Amsterdam, The Netherlands, June 6–9, 1988
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7918-4
  • Copyright © 1988 by ASME


For many years, there has been a significant effort, both experimental and theoretical, to better understand the rotating stall phenomenon. For very practical reasons, most of the experimental investigations have focussed on laboratory compressors with very low stage pressure ratios. The aim of the present study was to extend the range of available data to industrial-size compressors operating in a typical real life environment. This paper reports results of detailed flow measurements made on the first four stages of a 10 stage compressor operating as part of a turbojet engine mounted on a test stand. Hot sensor anemometer measurements made at a number of axial and tangential locations showed clear evidence of rotating stall in the front stages during part-speed operation of the engine. Stall cell configuration and rotative speed, and details of flow speed and angle at hub, mid and tip radii are presented in the paper. On the basis of the measurements it is concluded that (1) although rotating stall has its origins in a flow instability, it is a highly reproducible phenomenon, (2) reverse flow can occur within the cells, as has been reported by several other observers and (3) the cells retain an axial (as opposed to helical) configuration on passing from stage to stage through the compressor.

Copyright © 1988 by ASME
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