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An Inviscid-Viscous Interaction Treatment to Predict the Blade-to-Blade Performance of Axial Compressors With Leading Edge Normal Shock Waves PUBLIC ACCESS

[+] Author Affiliations
W. J. Calvert

National Gas Turbine Establishment, Farnborough, Hants, England

Paper No. 82-GT-135, pp. V001T01A056; 12 pages
doi:10.1115/82-GT-135
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7956-6
  • Copyright © 1982 by ASME

abstract

An inviscid-viscous interaction treatment has been developed to predict the blade-to-blade flow in axial compressors operating with supersonic inlet conditions and a normal shock wave at inlet to the blade passage. The treatment uses both direct and inverse modes of operation for the inviscid and viscous calculations, and thus it can model the separation of the suction surface boundary layer produced by the strong interaction with the shock wave. The inviscid flow is calculated by a time marching method and the viscous flow by integral methods for laminar and turbulent boundary layers.

Copyright © 1982 by ASME
This article is only available in the PDF format.

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