低雷诺数下跨声速转子流动失稳及附面层抽吸扩稳研究  

Research on flow instability of transonic compressor rotor and boundary suction effect at low Reynolds number

作　　者：夏钦斌[1] 王如根[1] 周敏[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7期1610-1615,共6页Journal of Aerospace Power

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.通过在该压气机转子叶片吸力面上不同的叶高和轴向弦长处进行抽吸,发现都可以很好的抑制附面层径向涡的发展,压气机转子的稳定工作范围明显扩大.此外还比较了不同的抽吸量对压气机的性能的影响.The flow instability of NASA Rotor 37 transonic compressor rotor at low Reynolds number was investigated by numerical simulation.The result shows that the boundary layer radial vortex becomes an important factor for causing compressor flow instability.It s found that the compressor stability range is obviously enlarged by suction on the blade suction surface at different blade heights and axial chords.The influence of suction mass on the characteristic of the compressor was also compared.

关 键 词：流动失稳 低雷诺数 附面层径向涡 抽吸 

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]