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Compressor Blade Boundary Layers in the Presence of Wakes FREE

[+] Author Affiliations
N. A. Cumpsty, Y. Dong, Y. S. Li

Cambridge University, Cambridge, England

Paper No. 95-GT-443, pp. V001T01A108; 16 pages
doi:10.1115/95-GT-443
From:
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME

abstract

Transition on compressor blades is strongly affected by the wakes from upstream blade rows and by the strong adverse pressure gradients which tend to make the laminar flow to separate. This paper outlines the processes involved and illustrates them with measurements on two different types of blade. Of particular importance is the calmed region which follows any turbulent patch created by a wake; the calmed region resists transition from other disturbances and is able to overcome strong adverse pressure gradients without separation.

Copyright © 1995 by ASME
This article is only available in the PDF format.

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