对跨音速转子附面层发展控制研究  

Research on Boundary Development Control at Transonic Compressor Rotor

作　　者：李勇[1] 王如根[1] 夏钦斌[1] 

机构地区：[1]空军工程大学工程学院,西安710038

出　　处：《汽轮机技术》2010年第1期32-34,38,共4页Turbine Technology

摘　　要：采用数值方法模拟了低雷诺数条件下NASA Rotor 37跨音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叶顶附近处进行抽吸,发现可以很好地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 triggering off the compressor flow instability. It＇ s found that the stability work rang is obviously enlarged by suction on the blade suction surface near the blade tip. The influence of suction mass to the characteristic of the compressor was compared.

关 键 词：压气机 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]