Role of Blade Passage Flow Structures in Axial Compressor Rotating Stall Inception PUBLIC ACCESS

[+] Author Affiliations
Donald A. Hoying

Air Force Research Laboratory, Wright-Patterson Air Force Base, Dayton, OH

Choon S. Tan, Huu Duc Vo

Massachusetts Institute of Technology, Cambridge, MA

Edward M. Greitzer

United Technologies Research Center, East Hartford, CT

Paper No. 98-GT-588, pp. V001T01A138; 11 pages
  • 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


The influence of three-dimensional flow structures within a compressor blade passage has been examined computationally to determine their role in rotating stall inception. The computations displayed a short length-scale (or spike) type of stall inception similar to that seen in experiments; to the authors’ knowledge this is the first time such a feature has been simulated. A central feature observed during the rotating stall inception was the tip clearance vortex moving forward of the blade row leading edge. Vortex kinematic arguments are used to provide a physical explanation of this motion as well as to motivate the conditions for its occurrence. The resulting criterion for this type of stall inception (which appears generic for axial compressors with tip-critical flow fields) depends upon local flow phenomena related to the tip clearance and it is thus concluded that the flow structure within the blade passages must be addressed to explain the stability of an axial compression system which exhibits such short length-scale disturbances.

Copyright © 1998 by ASME
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