涡轮叶片表面气膜出流的数值模拟  

Numerical Simulation for the Film Ejections of Turbine Vane

作　　者：干鹏[1] 任丽芸[1] 李宇[1] 刘火星[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室,北京100083

出　　处：《燃气涡轮试验与研究》2008年第4期10-15,共6页Gas Turbine Experiment and Research

摘　　要：深入理解气膜出流对涡轮叶栅气动性能和流场结构的影响对于冷却涡轮的设计具有重要意义。本文利用数值模拟手段对涡轮叶栅表面气膜出流与主流相互作用进行了研究,给出了冷却孔附近的三维流场,分析了叶片表面气膜冷却机理以及吹风比对气膜出流与主流相互作用的影响规律。研究结果表明,吹风比增大将导致叶栅内部流动损失增大,且压力面更为明显;当吹风比增大到一定程度,叶片两侧面上将出现掺混肾型涡流动结构,并且在压力面和吸力面诱导出旋向相反的诱导涡。Thorough understanding of film cooling effect on gas turbine cascade flow fields and aerodynamic performance is important in cooling turbine design. The interaction between film ejections and main flow was investigated by numerical simulation in this paper. The features of 3-D flow field near the cooling hole were presented. The mechanism of film cooling and the blowing ratio effect on the interaction between film ejections and main flow were analyzed. The results show that the flow loss increases with blowing ratio accretion, which is more evidently on pressure side. With blowing ratio rising to a certain level, kidney vortexes are appeared in two sides of the blade, and the counter rotating induced eddies appear in pressure side and suction side respectively.

关 键 词：涡轮 叶栅 气膜出流 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]