Abstract: The application of single and double vortex Generator Jets(VGJs) to a high speed compressor cascade for the aerodynamic performance and the action mechanism of flow control was studied using numerical simulation under different angle of attack，the aerodynamic performance parameters and end-wall flow distribution in the cascade were analyzed in detail. The simulation results show that，single jets and co-rotating jets have good characteristics for angle of attack，the control effect of the total pressure loss at outlet obviously increased and then decreased slightly with the angle of attack rising. For the case i=2°，the control effect of VGJs is the most significant which can make the total pressure loss reduce 11.0% with single jet. Counter-rotating jets have a poor result and lead a 3.9% growth of the total pressure loss for i=-4°. After using the VGJs，the passage vortex is divided into two parts by jet vortex，secondary passage vortex (PVⅡ) near the suction surface quickly flow into corner region. End-wall span vortex (SV) disappears and suction surface flow separation is delayed，but the spanwise flow on the suction surface is enhanced. The secondary flow in cascade is effectively controlled.

Key words: High speed compressor cascade；Vortex generator jet；End-wall flow；Angle of attack

摘要： 为了探究不同攻角下单孔以及双孔射流旋涡发生器 (VGJs) 对高速扩压叶栅气动性能的影响和作用机理，采用数值模拟的方法对栅内气动性能参数以及端区流动分布进行了较为详细的分析。数值结果表明:单孔以及同向双孔射流均具有较好的变攻角特性，随着攻角的增加控制效果先显著增加然后略微降低，在2°攻角条件下，VGJs使得总压损失降低最为明显，单孔射流达到11.0%。反向双孔射流的控制效果较差，在-4°攻角条件下甚至出现了3.9%的总压损失增长。采用射流旋涡发生器，射流旋涡(JV) 将通道涡分成两部分，靠近吸力面的次生通道涡 (PVⅡ) 很快汇入角区，端壁展向涡 (SV) 消失，吸力面分离被推迟，但吸力面上的展向运动显著增强，叶栅通道内的二次流动得到有效控制。

关键词: 高速扩压叶栅；射流旋涡；端区流动；攻角