NASA C3X叶片前缘气膜冷却的数值模拟

Numerical Simulation of Film Cooling of on the Leading Edge NASA C3X Blade

对NASA C3X叶片前缘部分建立了合理简化模型,在此基础上数值研究了流动参数和气膜孔斜角角度对前缘气膜绝热冷却效率的影响。结果表明:①在吹风比为0.5~2.5,不同吹风比下,以小吹风比的冷却效率较高,吹风比为0.75时效率最高;主流雷诺数为100000和200000时,大雷诺数比小雷诺数下的冷却效率高;主、射流温度比不同时,冷却效率随温度比增大而增大;主流湍流度对冷却效率影响较小。②取射流孔斜角分别为30°、45°和60°,随着射流角度增加冷却效率降低。

A reasonable simplification model was made for the leading-edge part of NASA C3X blade,and based on this model,the influence of flow parameters and the bevel angle of film hole on the adiabatic cooling efficiency was studied.The results showed that:①When the blowing ratio ranges from 0.5 to 2.5,the cooling efficiency of small blowing ratio is higher.When the blowing ratio is 0.75,the efficiency is the high-est;When the mainstream Reynolds number is 100000 and 200000,the large Reynolds number has higher cooling efficiency than the small Reynolds number.When the temperature ratios of the main and jet streams are different,the cooling efficiency increases with the increase of the temperature ratio;The mainstream turbulence has little effect on the cooling efficiency.②The bevel angles of the jet holes are 30°,45°and 60°,respectively,and the cooling efficiency decreases as the angle increases.