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为了获得吹风比对新型气膜冷却孔冷却效率的影响规律,利用Fluent软件求解Navier-Stokes方程,对吹风比分别为0.5、1.0、1.5和2.0时单入口-双出口孔射流冷却效率进行了数值模拟计算,得到了不同吹风比下的流场和冷却效率.结果表明:吹风比对冷却效率有很大影响;随着吹风比的提高,不同次孔方位角下的冷却效率变化规律也不相同;当次孔方位角γ=30°时,吹风比为1.0时的冷却效率最高;当γ=45°时,冷却效率随着吹风比提高而提高;当γ=60°时,冷却效率随着吹风比提高而降低;在研究高吹风比对气膜冷却效率的影响时,γ=45°最佳.
In order to obtain the effect of blow ratio on the cooling efficiency of a new film cooling hole, the Navier-Stokes equation was solved by Fluent software. The jet cooling efficiency of the single-inlet / double-outlet holes at blowing rates of 0.5, 1.0, 1.5 and 2.0 were respectively numerically The simulation results show that the blowing ratio has a great influence on the cooling efficiency, and the cooling efficiency varies with the blowing ratio at different sub-apertures in different azimuths ; When the sub-aperture azimuth γ = 30 °, the cooling efficiency is the highest when the blowing ratio is 1.0; when γ = 45 °, the cooling efficiency increases with the blowing ratio increasing; when γ = 60 °, The blowing ratio increased and decreased; when studying the effect of high blowing ratio on the film cooling efficiency, γ = 45 ° was the best.