叶顶射流对涡轮流场及气动性能影响  

Effects of Tip Injection on Turbine Flow Field and Aerodynamic Performance

作　　者：李文[1,2] 董平[1] 陈海生[1] 谭春青[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院研究生院,北京100190

出　　处：《工程热物理学报》2011年第10期1665-1668,共4页Journal of Engineering Thermophysics

摘　　要：通过对带有前缘气膜冷却的C3X涡轮叶片的传热和气动试验结果进行计算验证,表明所使用计算方法在对带有冷却射流的跨音涡轮压力及温度进行的预测具有较高的精度,在此基础上针对某型发动机低压涡轮,通过CFD数值模拟研究其叶顶冷却射流对叶顶泄漏流及涡轮性能的影响规律,并通过详细分析叶顶流动揭示该规律产生的原因;然后通过改变不同叶顶间隙大小,研究了间隙流和泄漏涡流动规律及叶顶间隙对叶顶冷却射流和透平性能影响,并通过其复杂流场分析揭示了其内在机理。The C3X gas turbine vanes cooled with leading edge films is simulated by Conjugate calculation methodology.The results show that the numerical results agree well with the experimentally measured data,which indicates the computation method is suitable to simulate transonic turbine. Then the verified computation method is used to investigate the effects of tip injection on the tip leakage and the aerodynamic performance of a low pressure turbine rotor.To obtain the mechanism, the tip flow and the tip leakage vortex are studied with different tip clearance height.

关 键 词：冷却射流 叶顶泄漏 低压涡轮 叶顶间隙 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V231.1