低雷诺数条件下跨声速转子轴向倾斜缝处理机匣扩稳研究  

Research on the effects of a transonic compressor rotor with axial skewedslots casing treatment at low Reynolds number

作　　者：夏钦斌[1] 王如根[1] 周敏[2] 王龙[1] 李勇[1] 郭飞飞[1] 

机构地区：[1]空军工程大学工程学院,西安710038 [2]北京航空工程技术研究中心,北京100076

出　　处：《航空动力学报》2010年第6期1389-1394,共6页Journal of Aerospace Power

基　　金：APTD研究项目(APTD-1504-04-07)

摘　　要：采用非定常数值方法对低雷诺数条件下50%,75%和100%三种不同轴向叠合量的轴向倾斜缝处理机匣结构对NASA Rotor 37跨声速压气机转子的扩稳效果进行了研究.结果表明,引入处理机匣后,附面层径向涡得到了很好的抑制,由附面层径向涡所引发的叶顶阻塞区大为减小,虽然又引发了由叶顶间隙涡对叶顶所造成的阻塞,但引入处理机匣后对压气机稳定性仍有较大的改善,能有效提高压气机转子的失速裕度.The effects of NASA Rotor 37 transonic compressor rotor with 50%,75% and 100% axial congruence skewed slots casing treatment at low Reynolds number were investigated by unsteady numerical simulation.The result shows that the boundary layer radial vortex is well controlled and the blockage zone due to boundary layer separation is notably reduced.It＇s also found that the blockage zone is caused due to the tip leakage vortex.The stall margin of the compressor rotor with axial skewed slots is obviously improved,contributing to the compressor stability.

关 键 词：压气机 流动失稳 低雷诺数 机匣 附面层径向涡 叶顶间隙流 

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]