叶片冲击/气膜复合冷却的数值研究  

Numerical Study on Impingement/Film Composite Cooling of Turbine Blade

作　　者：王昌叶 刘钊[1] 叶绿[1] 丰镇平[1] 

机构地区：[1]西安交通大学能源与动力工程学院叶轮机械研究所,西安710049

出　　处：《工程热物理学报》2015年第1期55-59,共5页Journal of Engineering Thermophysics

基　　金：中国博士后基金资助(No.2013M542345)

摘　　要：应用数值方法研究了燃气轮机透平叶片冲击/气膜复合冷却特性。首先对湍流模型进行了考核,根据与已有试验数据的比较,数值计算选用与试验结果吻合最好的SST k-ω模型进行。然后分析了不同吹风比下叶片前缘内部冲击冷却和外部气膜冷却的流动和换热特性。结果表明:冲击室内,平均努塞尔数在叶根处最低,沿叶高方向逐渐增大,从某一叶高处开始在一定的范围内波动。随着吹风比的提高,冲击室内周向平均努塞尔数及其峰值都增大,气膜孔附近的气膜冷却效率降低,气膜孔下游的气膜冷却效率增加。The flow and heat transfer characteristics of impingement and film composite cooling in gas turbine blade was investigated numerically.Firstly,by comparing with available experimental data,the relative performance of four turbulence models for predicting impingement and film composite cooling is studied,and the SST k-ω model was adapted for the calculation,then the effect of blowing ratio on flow and heat transfer performances of impingement and film cooling in blade leading edge were studied.The results show that the lowest value of streamwise averaged Nusselt number of the internal surface appears at the hub,and the averaged Nusselt number continually increases along the spanwise from the hub to middle span,and then its value fluctuates smoothly in a certain range.With the increasing in blowing ratio,the Nusselt number of the internal surface increases,the film cooling effectiveness of the near film holes regions decreases,but the film cooling effectiveness on the far downsteam of film holes increases.

关 键 词：冲击冷却 气膜冷却 复合冷却 冷却效率 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程]