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RESEARCH PAPERS

Film Cooling of the Gas Turbine Endwall by Discrete-Hole Injection

[+] Author and Article Information
M. Y. Jabbari, K. C. Marston, E. R. G. Eckert, R. J. Goldstein

Department of Mechanical Engineering, University of Minnesota, Minneapolis, MN 55455

J. Turbomach 118(2), 278-284 (Apr 01, 1996) (7 pages) doi:10.1115/1.2836637 History: Received February 09, 1994; Online January 29, 2008

Abstract

Film cooling performance for injection through discrete holes in the endwall of a turbine blade is investigated. The effectiveness is measured at 60 locations in the region covered by injection. Three nominal blowing rates, two density ratios, and two approaching flow Reynolds numbers are examined. Analysis of the data reveals that even 60 locations are insufficient for the determination of the field of film cooling effectiveness with its strong local variations. Visualization of the traces of the coolant jets on the endwall surface, using ammonium-diazo-paper, provides useful qualitative information for the interpretation of the measurements, revealing the paths and interaction of the jets, which change with blowing rate and density ratio.

Copyright © 1996 by The American Society of Mechanical Engineers
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