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 exit Mach numbers are 0.7, 0.9, and 1.1, from high subsonic to transonic conditions. Nitrogen, carbon dioxide, and an 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 radial-angle cylindrical holes around the leading edge and two rows of compound-angle-shaped holes on the suction side. A pressure-sensitive paint technique is used to obtain the film cooling effectiveness distributions from suction-side holes and the contribution from leading-edge showerhead holes. This work shows the effects of the blowing ratio, density ratio, and exit Mach number on the film cooling 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.
Transonic Turbine-Vane Film Cooling with Showerhead Effect Using Pressure-Sensitive Paint Measurement Technique
Journal of Thermophysics and Heat Transfer ; 32 , 3 ; 637-647
2018-02-28
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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