跨声速压气机低雷诺数下流动失稳机制研究  

Research on flow instability mechanism of transonic compressor at low Reynolds number

作　　者：王如根[1] 周敏[1] 赵英武[1] 夏钦斌[1] 曾令君[1] 

机构地区：[1]空军工程大学工程学院,西安710038

出　　处：《航空动力学报》2009年第2期414-419,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：数值模拟了低雷诺数下跨声速压气机设计转速下内部流场特性.结果表明:在压气机流场内部存在从叶根向叶顶运动的附面层径向涡流,它由叶根附面层转捩区内的分离气流引发,从叶根向叶顶发展,并在叶顶聚集.随着雷诺数下降,该附面层径向涡的作用范围不断增大,在叶顶形成大面积分离区,在激波和间隙泄漏流诱发的阻塞尚未充分发展起来之前,该分离区产生的通道阻塞起主导作用,成为低雷诺数条件下影响压气机流动失稳的关键因素.The effect of low Reynolds number on the flow instability mechanism of transonic compressor was studied numerically. The result shows that the radial vortex exists in the compressor inner flow field, which is formed from separation flow in the boundary layer transition zone. Under centrifugal force, radial vortex flows from blade hub to blade tip and converges at the blade tip flow field. As Reynolds number decreases, the effect range of radial vorte is extended, a bigger boundary layer separation zone is formed at the blade tip, which is decisive to the flow instability of transonic axial compressor before blockage zone due to shock and tip leakage flow is fully developed.

关 键 词：流动失稳机制 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]