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Effects of the Inlet Endwall Boundary Layer on 3-D Flows and Loss Evolution in a Linear Turbine Cascade FREE

[+] Author Affiliations
J. Tominaga, E. Outa

Waseda University, Tokyo, Japan

Atsumasa Yamamoto

National Aerospace Laboratory, Tokyo, Japan

Paper No. 95-GT-188, pp. V001T01A047; 10 pages
doi:10.1115/95-GT-188
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

A three-dimensional Navier-Stokes computation was made for investigating internal flow phenomena of a linear turbine cascade, and the results were compared with the test data obtained inside the cascade passage. The present code was found to fairly well simulate the experimental data, as well as various vortices being generated in the cascade passage. In this paper, detailed mechanisms of the loss generation are discussed mainly from the computational point of view.

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

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