为了研究跨声速压气机内部流动失稳对压气机性能的影响，对跨声速轴流压气机NASA转子37进行三维定常数值模拟，研究不同设计转速下跨声速轴流压气机稳定运行及内部流动失稳现象。研究发现：转速不变时近堵塞点的等熵效率高于近失速点；随着转速降低，压气机稳定运行范围变宽、效率增大及流动损失变小；压气机叶栅通道出现堵塞情况的叶高截面范围随着转速的降低而逐渐增大，这导致压气机叶片在近失速点处的流动失稳情况变严重。

In order to study the effect of internal flow instability of the compressor on its performance,the threedimensional steadystate numerical simulation of NASA rotor37 of a transonic axial compressor was carried out,the phenomena of the stable operation and internal flow instability of the transonic axial compressor at different design speeds were studied.It is found that the isentropic efficiency near the plugging point is higher than that near the stall point when the rotating speed is constant.As the speed decreases,the stable operating range of the compressor becomes wider,the efficiency increases and the flow loss becomes smaller.However,the section range of the blade height where the compressor cascade passage is blocked gradually increases with the decrease of the rotating speed,which leads to the flow instability of the compressor blade near the stall point becoming more serious.

V235

陕西省科学技术厅重点项目（2017ZDXM-GY-138）；陕西省科学技术厅一般项目（2020JM-600）；陕西省教育厅科研项目（19JK0172）