低速轴流压气机尾流撞击效应的数值模拟  

Numerical investigation of wake impact effect in low-speed axial compressor

作　　者：郑新前[1] 周盛[1] 

机构地区：[1]北京航空航天大学航空发动机气动热力重点实验室,北京100083

出　　处：《推进技术》2004年第5期421-425,共5页Journal of Propulsion Technology

基　　金：北京航空航天大学博士生创新研究基金;国家自然科学基金(10072008)。

摘　　要：利用二维数值模拟研究了低速轴流压气机上游尾迹对下游相邻叶排的非定常分离流场的影响。研究表明:满足一定通过频率和亏损幅值条件的尾迹能够有效抑制下游相邻叶排尾缘涡的生成,达到控制或是推迟附面层非定常分离的目的,从而使得流场时均性能大幅度的提高,损失系数降低了40 2%,功损比增加93%。为固有非定常潜能的利用提供了一类新途径。By using a Reynolds-averaged two-dimensional computation, the effect of upstream wake on unsteady separated flow field of downstream adjacent vanes was investigated in low-speed axial compressor. The results indicate that the generation of trailing-vortex of downstream adjacent vanes could be restrained effectively by upstream wake when the passing frequency and the amplitude of wake defect satisfy some conditions, associated with a significant enhancement of time-averaged aerodynamic performance: reducing loss coefficient by 40.2% and the ratio of loading coefficient and increasing loss coefficient by 93%. Thus, an approach was available to utilize the potentiality of intrinsic unsteady flow.

关 键 词：压气机 非定常流 分离流 尾流撞击效应 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]