Film Cooling With Compound Angle Holes: Adiabatic Effectiveness

[+] Author and Article Information
D. L. Schmidt, B. Sen, D. G. Bogard

Mechanical Engineering Department, University of Texas at Austin, Austin, TX 78712

J. Turbomach 118(4), 807-813 (Oct 01, 1996) (7 pages) doi:10.1115/1.2840938 History: Received February 09, 1994; Online January 29, 2008


Film cooling effectiveness was studied experimentally in a flat plate test facility with zero pressure gradient using a single row of inclined holes, which injected high-density, cryogenically cooled air. Round holes and holes with a diffusing expanded exit were directed laterally away from the free-stream direction with a compound angle of 60 deg. Comparisons were made with a baseline case of round holes aligned with the free stream. The effects of doubling the hole spacing to six hole diameters for each geometry were also examined. Experiments were performed at a density ratio of 1.6 with a range of blowing ratios from 0.5 to 2.5 and momentum flux ratios from 0.16 to 3.9. Lateral distributions of adiabatic effectiveness results were determined at streamwise distances from 3 D to 15 D downstream of the injection holes. All hole geometries had similar maximum spatially averaged effectiveness at a low momentum flux ratio of I = 0.25, but the round and expanded exit holes with compound angle had significantly greater effectiveness at larger momentum flux ratios. The compound angle holes with expanded exits had a much improved lateral distribution of coolant near the hole for all momentum flux ratios.

Copyright © 1996 by The American Society of Mechanical Engineers
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