尾迹对压气机转子性能影响的非定常数值模拟  

Unsteady Numerical Simulation of Wake Effects on Compressor Rotor Performance

作　　者：霍磊[1] 牛为民 任丽芸[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室,北京100083 [2]哈尔滨东安集团航空发动机研究所,黑龙江哈尔滨150066

出　　处：《燃气涡轮试验与研究》2008年第1期26-32,共7页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(50546013)

摘　　要：采用三维粘性非定常数值模拟方法,研究了上游尾迹对轴流压气机转子性能及其尖部非定常流动的影响。结果表明,在一定情况下,上游静子尾迹与转子内部流动的非定常相互作用,有可能改善近失速点的气动性能,如转子压比和效率升高,工作范围增大。其原因主要为:上游静子尾迹使转子尖区一次泄漏涡强度减弱,减少了二次泄漏涡强度或抑制了二次泄漏涡的产生,最终导致尖区损失减少;此外,尾迹使尖区激波位置后移,改变了尖部弦向的负荷分布,最终导致压气机稳定工作范围增大。3D unsteady viscous numerical simulation was employed to investigate the influences of upstream wakes on axial flow compressor rotor performance and rotor tip unsteady flow. The numerical results indicate that, under certain conditions, the interaction of upstream wakes and rotor internal flow results in rotor pressure ratio and efficiency increasing also extends rotor operation range. The performance increase has been found at near stall conditions. The stator wakes weaken the intensity of rotor tip region primary leakage vortices; also decrease the intensity of secondary leakage vortices, which lead to a reduction of tip region losses. On the other hand, the shock wave position of tip region moves backwards, the loading distributions of tip region have been changed, which lead to the increase of rotor operation range.

关 键 词：压气机 叶尖泄漏涡 尾迹 非定常流动 数值模拟 

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]