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Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence PUBLIC ACCESS

[+] Author Affiliations
Y. Elazar, R. P. Shreeve

Naval Postgraduate School, Monterey, CA

Paper No. 89-GT-131, pp. V001T01A054; 10 pages
doi:10.1115/89-GT-131
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

A detailed two-component LDV mapping of the flow through a controlled diffusion compressor cascade at low Mach number (∼0.25) and Reynolds number of about 7×105, at three inlet air angles from design to near stall, is reported. It was found that the suction side boundary layer reattached turbulent after a laminar separation bubble, and remained attached to the trailing edge even at the highest incidence, at which losses were 3 to 4 times the minimum value for the geometry. Boundary layer thickness increased to fill 20% of the blade passage at the highest incidence. Results for pressure-side boundary layer and near wake are also summarized. Information sufficient to allow preliminary assessment of viscous codes is tabulated.

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

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