Transonic Turbine-Vane Film Cooling with Showerhead Effect Using Pressure-Sensitive Paint Measurement Technique
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© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. This work focuses on the parametric experimental study of film cooling effectiveness on the suction side of a scaled turbine vane. The experiments are performed in a five-vane annular sector cascade blowdown facility. The controlled exitMach numbers are 0.7, 0.9, and 1.1, fromhigh subsonic to transonic conditions. Nitrogen, carbon dioxide, and an argon/sulfurhexafluoride mixture are used to investigate the effects of density ratios, from 1.0, 1.5 to 2.0. Three row-averaged blowing ratios in the range of 0.7, 1.0, and 1.6 are studied. The test vane includes three rows of radialangle cylindrical holes around the leading edge and two rows of compound-angle-shaped holes on the suction side. Apressure-sensitive paint technique is used to obtain the filmcooling effectiveness distributions fromsuction-side holes and the contribution from leading-edge showerhead holes. This work shows the effects of the blowing ratio, density ratio, and exitMach number on the filmcooling effectiveness, as well as its interaction with a potential shock wave. The results indicate that, when the cooling holes are located in a critical region on the vane suction surface, the parametric effect on film cooling performance will significantly deviate from the common trend for a typical hole geometry.
author list (cited authors)
Shiau, C., Chowdhury, N., Han, J., Mirzamoghadam, A. V., & Riahi, A.
complete list of authors
Shiau, Chao-Cheng||Chowdhury, Nafiz HK||Han, Je-Chin||Mirzamoghadam, Alexander V||Riahi, Ardeshir