跨音速透平叶栅尾缘劈缝射流的数值研究  

Simulation Study of the Trailing Edge Slot Ejection on a Transonic Turbine Cascade

作　　者：姚世传 陈榴[1] 轩笠铭 施鎏鎏 戴韧[1] 

机构地区：[1]上海理工大学能源与动力工程学院,上海200093

出　　处：《动力工程学报》2018年第2期92-97,共6页Journal of Chinese Society of Power Engineering

基　　金：国家自然科学基金资助项目(51276116;11602143)

摘　　要：采用Spalart-Allmaras(S-A)湍流模型对跨音速导叶尾缘劈缝射流的定常流动结构进行了模拟分析,研究不同尾缘射流压比对尾缘激波结构与强度、尾迹形态、各种能量损失的影响规律.结果表明:劈缝射流可以减小尾迹宽度与低速峰值,降低尾缘燕尾波的强度,射流对压力面侧激波的削弱作用更大;射流使燕尾波的形成位置更接近尾缘,导致燕尾波张角增大;射流可以降低叶栅的总动能损失,压比对激波损失和尾迹损失的影响更明显,但对边界层损失的影响较小;根据叶栅出口的状态可知,存在一个最佳的射流压比.Spalart-Allmaras （S-A） turbulence model was used to simulate and analyze the steady flow struc- ture of trailing edge slot ejection on a transonic turbine cascade, while a study was conducted on the effects of different pressure ratios of trailing edge ejection on following parameters, such as the structure and in- tensity of shock, the structure of wake and various energy losses, etc. Results show that the wake width, the lowest velocity magnitude, and the intensity of trailing edge shock can all be reduced by slot ejection, which has relatively larger weakening effect on the shock at pressure side. The ejection causes the forma- tion position of shock to approach the trailing edge, leading to the increase of the shock angle. Total kinet- ic energy loss of the cascade can be reduced by ejection. The shock loss and wake loss are more sensitive to the ejection pressure ratio than the loss in boundary layer. According to the state of cascade exit, there ex- ists an optimum ejection pressure ratio in the transonic turbine.

关 键 词：跨音速透平 尾缘劈缝 激波强度 尾迹形态 气动性能 

分 类 号：TK474.7[动力工程及工程热物理—动力机械及工程]