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Cooling-Air Injection Into Secondary Flow and Loss Fields Within a Linear Turbine Cascade FREE

[+] Author Affiliations
A. Yamamoto

National Aerospace Laboratory, Chofu, Tokyo, Japan

Y. Kondo, R. Murao

Aoyama University, Setagaya, Tokyo, Japan

Paper No. 90-GT-141, pp. V001T01A045; 10 pages
doi:10.1115/90-GT-141
From:
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME

abstract

In order to understand overall performance and internal flows of air-cooled turbine blade rows, flows in a model linear cascade were surveyed with secondary air injection from various locations of the blade surfaces. The secondary air interacted with the cascade passage vortices and changed the loss distribution significantly. The cascade overall loss decreased when the air was injected along the mainstream and increased when the air was injected against the mainstream from some locations of the blade leading edge. Effects on overall kinetic energy of the secondary flows and on the cascade outlet flow angle were also discussed in this paper.

Copyright © 1990 by ASME
This article is only available in the PDF format.

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