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RESEARCH PAPERS

Gas Turbine Film Cooling: Flowfield Due to a Second Row of Holes

[+] Author and Article Information
A. K. Sinha, D. G. Bogard, M. E. Crawford

University of Texas at Austin, Austin, TX 78712

J. Turbomach 113(3), 450-456 (Jul 01, 1991) (7 pages) doi:10.1115/1.2927895 History: Received January 11, 1990; Online June 09, 2008

Abstract

Flowfield measurements with relevance to gas turbine film cooling were carried out behind a second row of holes located 40 hole diameters downstream of a first row and staggered with respect to it. The effects of the thicker boundary layer and that of injection from the first row were examined. Experiments were carried out for jet-to-mainstream density ratios of 1 and 2 and results compared to those obtained by Pietrzyk et al. (1989, 1990) behind the first row. Results show that the dominant structures identified in the flowfield downstream of the first row were also present behind the second row. Due to the thicker boundary layer, though, the mean flowfield and the turbulence and shear stress fields were altered. One of the significant results was that the thicker boundary layer enables the jets to penetrate deeper into the mainstream.

Copyright © 1991 by The American Society of Mechanical Engineers
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