Film Cooling of Gas Turbine Blades: A Study of the Effect of Large Temperature Differences on Film Cooling Effectiveness

[+] Author and Article Information
M. A. Paradis

Department of Mechanical Engineering, Laval University, Quebec, P.Q., Canada

J. Eng. Power 99(1), 11-20 (Jan 01, 1977) (10 pages) doi:10.1115/1.3446240 History: Received November 14, 1975; Online July 14, 2010


Experiments have been performed on the film cooling of gas turbine blades in order to study the influence of large temperature differences on the effectiveness of film cooling. A two-dimensional flat plate model was tested in a stream of 1000 K combustion gases flowing at between 110 and 170 m/s. The model was cooled on both sides by jets of air coming from flush angled slots. The range of velocity ratios Uc /Ug covered was from 0.3 to 1.7 and the range of blowing rates was between 0.5 and 5. Film cooling effectiveness was measured and boundary layer traverses were performed. It has been found that once radiation and conduction effects are taken into account, the simple equations proposed by previous workers for the constant property case could be used with little error.

Copyright © 1977 by ASME
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