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Tip Clearance Flow Induced Endwall Boundary Layer Separation in a Single–Stage Axial–Flow Low–Speed Compressor

[+] Author Affiliations
Horst Saathoff, Udo Stark

Technical University Braunschweig, Germany

Paper No. 2000-GT-0501, pp. V001T03A070; 10 pages
doi:10.1115/2000-GT-0501
From:
  • ASME Turbo Expo 2000: Power for Land, Sea, and Air
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Munich, Germany, May 8–11, 2000
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7854-5
  • Copyright © 2000 by ASME

abstract

The paper describes an investigation of the overtip end-wall flow in a single–stage axial–flow low–speed compressor utilizing an oil flow technique and a periodic multisampling pressure measurement technique. Representative oil flow pictures and ensemble averaged casingwall pressure distributions with standard deviations — supplemented by selected endwall oil flow pictures from a corresponding 2D compressor cascade — are shown and carefully analysed. The results enable the key features of the overtip endwall flow to be identified and changes with flow rate — or inlet angle — to be determined.

Copyright © 2000 by ASME

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