低雷诺数下跨声速转子流动失稳及周向槽处理机匣扩稳  

Investigation on flow instability of transonic compressor rotor and the effects of CGCT on stall margin at low Reynolds number

作　　者：夏钦斌[1] 王如根[1] 李勇[1] 郭飞飞[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038

出　　处：《推进技术》2010年第3期340-344,共5页Journal of Propulsion Technology

基　　金：APTD研究项目(APTD-1504-04-07)

摘　　要：采用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场。结果表明,附面层径向涡是该压气机转子流动失稳的一个很重要的原因。根据该压气机转子低雷诺数条件下流动失稳的特点,研究了周向槽处理机匣结构对其性能的影响。结果表明,引入处理机匣后,附面层径向涡得到一定程度的抑制,由附面层径向涡所引发的叶顶阻塞区有所减小,提高了压气机转子的失速裕度。The flow instability of NASA Rotor 37 transonic compressor rotor at low Reynolds number was investigated by numerical simulation.The results show that the boundary layer radial vortex becomes an important factor for triggering off the compressor flow instability.The effects of the transonic compressor rotor with circumferential groove casing treatment were investigated.The results show that the boundary layer radial vortex is controlled to some extent and the blockage zone due to boundary layer separation is reduced,and the stall margin of the compressor rotor is increased.

关 键 词：压气机 流动失稳 低雷诺数 机匣处理 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]