Abstract: The single-passage steady and multi-passages steady/unsteady numerical simulation of the transonic axial-flow compressor-NASA Rotor 37 were investigated.The numerical results agreed well with experimental test data with estimation of the global performance.For the multi-passages unsteady computation,detailed analysis of the internal flow field with the NASA Rotor 37 led to some preliminary conclusion for unsteady behavior of the tip leakage flow,the interaction of the vortex and the shock wave and trigger spike type rotating stall inception.It is the forward spillage of the tip leakage flow at the leading edge that induces the spike stall inception.The rotating stall cell is first generated at the blade tip region and the rotating speed is about 80% of the rotor speed.As the mass flow ratio decreases,the rotating stall cell is far developed.At the stalled passages,the passage shock is fully detached from the leading edge,and the reverse tip clearance flow is initiated at trailing edge plane.When the rotor is fully stalled,the rotating stall cell is covered almost 4 passages in blade to blade direction,and it occupies nearly half of the blade span.

Key words: Transonic compressor;Rotor;Stalling;Leakage;Numerical simulation

摘要： 通过对跨声速轴流压气机NASA转子37进行单通道定常及多通道定常、非定常数值模拟,单通道定常数值模拟结果与实验结果能较好吻合。多通道非定常数值模拟结果显示,间隙泄漏流及其与激波干涉的非定常振荡,触发突尖型旋转失速先兆,具体表现为叶顶前缘间隙泄漏流溢出。失速团首先在叶顶处形成,且速度约为80%转速。随着流量的下降,失速团进一步发展,在失速通道内,激波与叶片前缘完全分离,且在叶片尾缘出现回流。当转子完全数值失速时,失速团周向尺度约为4个通道,且径向占据约半个叶高。

关键词: 跨音速压气机;转子;失速;泄漏;数值仿真