低雷诺数下跨声速压气机转子失速工况时流动失稳触发过程研究  

Research on flow instability triggering process at stall condition of transonic compressor rotor at low Reynolds number

作　　者：周敏[1,2] 王如根[1] 白云[1] 王学德[1] 武卫[1] 

机构地区：[1]空军工程大学工程学院,西安710038 [2]空军装备研究院航空装备研究所,北京100076

出　　处：《航空动力学报》2009年第6期1379-1384,共6页Journal of Aerospace Power

基　　金：APTD研究项目(APTD-1504-04-07);空军工程大学工程学院优秀博士学位论文创新基金(BC07006)

摘　　要：采用非定常数值方法模拟了低雷诺数条件下NASA Rotor 37跨声速压气机转子内部流动失稳机制.结果表明,随着压气机失速工况的推进,附面层径向涡不断扩大和增强,由附面层径向涡引发的叶顶附面层分离阻塞区不断向叶片前缘移动,直至与叶顶压力面前缘附近由激波和间隙泄漏流诱发的阻塞区相结合,使叶顶通道来流完全被阻塞,最终触发压气机流动失稳.The flow instability triggering process at stall condition of NASA Rotor 37 transonic compressor rotor at low Reynolds number was investigated by unsteady numerical simulation. The result shows that the effect range of boundary layer radial vortex is extended, the boundary layer separation blockage zone due to radial vortex is assembled at the blade tip, as the stall condition develops, the boundary layer separation blockage zone moves to the blade leading edge, and combines with blockage zone due to shock and tip leakage flow. So the blade tip passage is fully blocked, and compressor flow instability is triggered off.

关 键 词：跨声速压气机 流动失稳 雷诺数 附面层径向涡 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]