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。周向槽处理机匣结构对压气机流场的改善较为有限,而引入抽吸处理机匣后,抽吸槽可以将叶顶间隙涡和附面层径向涡及其引发的低能阻塞流团抽吸至处理槽内,叶顶流场大为改善,有效地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.Result shows 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 grooves casing treatment and suction groove casing treatment were investigated.It is showed that the effects of circumferential grooves are not very obvious.The suction groove casing treatment are much more effective,the blockage zones due to boundary layer radial vortex and tip leakage vortex can be suctioned to the suction groove,and the stall margin of the compressor rotor is increased.
出处
《空气动力学学报》
CSCD
北大核心
2011年第2期189-193,共5页
Acta Aerodynamica Sinica
基金
APTD研究项目(APTD-1504-04-07)
关键词
压气机
流动失稳
低雷诺数
机匣处理
附面层径向涡
compressor
flow instability
low Reynolds number
casing treatment
boundary layer radial vortex
