气膜孔角度对动叶前缘冲击/气膜复合冷却的影响

Effect of Film Hole Angle on Combined Impingement and Film Cooling on a Blade Leading Edge Model

本文针对GE-E3第一级动叶前缘的冲击/气膜复合冷却结构进行了热流耦合数值研究。采用标准k-ω湍流模型,分析了前缘气膜孔对称布置时,其角度对透平动叶前缘冲击/气膜复合冷却特性的影响;在五种冷气质量流量比(MFR=0.005,0.010,0.016,0.020,0.025)下,研究了气膜孔在不同角度(β=20°,25°,30°,40°,50°,60°)时的透平动叶前缘冷却换热效果。研究结果表明:在本文研究范围内,气膜孔角度越小,透平动叶前缘的平均综合冷却效率越高;随着冷气质量流量比增大,透平动叶前缘的平均综合冷却效率逐渐提高。

In this paper,conjugate heat transfer numerical simulations about the combined impingement/film cooling structure on the leading edge of the GE-E3 first-stage blade were carried out.The standard k-ω turbulence model was adopted,and the effect of film hole angle with symmetrical arrangement on the combined impingement/film cooling characteristics on the turbine blade leading edge were analyzed;Under the five coolant mass flow ratios(MFR=0.005,0.010,0.016,0.020,0.025),the cooling and heat transfer performance on the turbine blade leading edge at different film hole angles(β=20°,25°,30°,40°,50°,60°) were studied.The results showed that:According to studied cases in this paper,the smaller the film hole angle is,the higher the area-averaged overall cooling effectiveness on the turbine blade leading edge is;As the coolant mass flow ratio increases,the area-averaged overall cooling effectiveness on the turbine blade leading edge gradually increases.