附面层抽吸对低雷诺数下压气机稳定性的影响  

Boundary Suction Effect on Compressor Instability at Low Reynolds Number

作　　者：王如根[1] 周敏[1] 夏钦斌[1] 

机构地区：[1]空军工程大学工程学院,陕西西安710038

出　　处：《燃气涡轮试验与研究》2010年第2期1-4,共4页Gas Turbine Experiment and Research

摘　　要：数值模拟了低雷诺数下附面层抽吸流动控制对跨声速压气机稳定性的影响。低雷诺数下附面层径向涡及其诱发的叶顶分离阻塞触发压气机流动失稳,通过在NASA Rotor 37跨声速轴流压气机转子叶片吸力面上设计抽吸槽,探讨了抽吸流动控制对低雷诺数下压气机性能和稳定性的影响,并对比分析了抽吸前后压气机流场特性的变化和抽吸流动控制提高低雷诺数下跨声速轴流压气机稳定性的作用机理。The boundary suction effect on compressor instability at low Reynolds number was investigated by numerical simulation. The result shows that the compressor instability is triggered off by the boundary layer radial vortex. Then a suction slot was designed on the suction surface of the transonic compressor NASA Rotor 37. The boundary suction control effect on compressor instability at low Reynolds number was discussed, and the analysis of compressor inner flow field characteristic was conducted to identify the physical mechanism of suction control at low Reynolds number.

关 键 词：跨声速压气机 附面层抽吸 低雷诺数 径向涡 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]