整体涡对跨声速单转子性能和稳定性影响  

Effect of bulk swirl on performance and stability of transonic single rotor

作　　者：屠宝锋[1,2] 胡骏[1,2] 张凯[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016 [2]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2016年第9期2233-2238,共6页Journal of Aerospace Power

基　　金：航空基金(2015ZB52018);中央高校基本科研业务费专项资金(NS2014021)

摘　　要：为研究整体涡影响轴流压气机性能和稳定性的机理,设计了一种叶片式旋流发生器,并对旋流发生器和跨声速单转子进行了联合数值模拟研究.计算结果表明:反向整体涡导致堵塞点流量、进口攻角和总压比增加,效率和稳定工作范围降低;同向整体涡导致堵塞点流量、进口攻角、总压比和稳定工作范围减小,效率增加;反向整体涡导致50%叶高以上吸力面附面层分离以及叶尖泄漏流堵塞加剧是压气机失稳的主要原因.In order to investigate the effect of bulk swirl on performance and stability of axial compressor, blade swirl generator was designed and numerically simulated with a tran- sonic single rotor. The results showed that counter-rotating bulk swirl caused significant drop in coefficient and stall margin and increase in choke mass flow, angle of attack and total pressure ratio. Co-rotating bulk swirl led to decrease of choke mass flow, attack angle, total pressure ratio and stable operating range, and increase of coefficient. Co-rotating bulk swirl caused suction surface boundary layer separation beyond 50% blade span, and more serious tip leakage blocking, contributing a lot to unstable compressor.

关 键 词：压气机 跨声速 整体涡 旋转发生器 稳定性 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]