尾流撞击效应对轴流压气机下游叶排涡面的影响  

Investigation of the effect of wake impact effect on vortex sheets of the downstream blade row in axial compressor

作　　者：周晓勃[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,北京100191

出　　处：《航空动力学报》2009年第3期608-614,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(10477002)

摘　　要：针对某高负荷高压压气机末级,通过研究上游转子尾迹涡面周期性扫掠对下游静子涡面的影响,从涡面非定常作用的角度分析流场时空结构.结果表明,流场性能的改善与涡面时空结构相对应,尾迹涡面同分离涡面的相互作用可显著降低流动损失;与上游尾迹涡面发生耦合的是叶片尾缘旋涡交替脱落频率而非吸力面前缘分离涡不稳定频率.The flowfield in axial compressor is characterized by unsteady vortex flow due to the relative motion of the blade rows.The upstream unsteady wake flow changing periodically is responsible for the airfoil aerodynamic efficiency and thus for the overall performance of the aeroengine.This paper examines the influence of such unsteadiness of upstream wake impact on the development of vortex sheets of downstream blades in a highly loaded HPC(High pressure compressor).The results of this study indicate that the ...

关 键 词：轴流压气机 流场时空结构 尾流撞击效应 涡面 

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]