Numerical Investigation on Film Cooling Performance of Turbine Blade with Asymmetrical Fan-shaped Holes

Abstract

Abstract: A numerical study is conducted to investigate the effect of the lateral diffusion angle of fan-shaped holes on the blade film cooling effectiveness at the suction and pressure surfaces. The baseline fan geometry has a 20° lateral diffusion and 10° laidback expansion. Film cooling effectiveness for asymmetrical fan-shaped holes is studied at different blowing ratios (from 0.44 to 2.67). Under the same total lateral diffusion angle of fan-shaped holes, the coolant jet penetration from the asymmetrical fan-shaped holes is equal to that from baseline fan geometry, but the film coverage in lateral direction is improved a little, which is obvious at the higher blowing ratio. And the asymmetrical fan-shaped holes are suitable to be applied to the pressure surface of turbine blade

Key words: Aerospace propulsion system, Asymmetrical fan-shaped holes, Fan-shaped holes, Film cooling, Turbine blade, energy saving, pressure and flow compound control, speed variable control, electro-hydraulic power source

CLC Number:

V231

XU Hongyan;ZHANG Jingzhou;YAO Yu. Numerical Investigation on Film Cooling Performance of Turbine Blade with Asymmetrical Fan-shaped Holes[J]. , 2011, 47(18): 152-157.

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http://www.cjmenet.com.cn/EN/Y2011/V47/I18/152

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Numerical Investigation on Film Cooling Performance of Turbine Blade with Asymmetrical Fan-shaped Holes

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