【摘要】 采用试验与数值模拟相结合的方法,研究了某超声速涡轮导向叶栅尾缘冷气喷射对叶栅流场结构的影响。数值模拟时,使用环形叶栅模型近似模拟平面叶栅内的流动。研究结果表明:数值模拟结果与试验结果吻合较好;尾缘冷气喷射可减少主气流在尾缘停滞区的能量耗损,削弱叶栅尾缘处的内边缘激波,叶栅气动效率随冷气量的增加先增大后减小;尾缘冷气喷射对叶栅出口附近气流角的周向分布有影响,但对质量平均的叶栅出口气流角基本无影响。更多还原

【Abstract】 The influence of cooling jet from a supersonic turbine guide vane cascade trailing-edge on the cascade flow-field was investigated by using simulation results and test results.An annular cascade model was used to simulate the flow-field in the plane cascade approximately.The results show that the dissipation of the main stream energy in the trailing edge stagnation region and the strength of the shock wave located at the pressure side of the trailing edge can be reduced by the trailing-edge coolant jet.The aerodynamic efficiency of the cascade will increase firstly and then decrease while the coolant ejection mass ratio increases.The numerical simulation results are good agreement with test results.The circumferential distribution of flow angle located at cascade exit is influenced by trailing edge coolant ejection,while the outlet flow angle at cascade with averaged mass is not.更多还原