变冲角条件下等离子体对扩压叶栅性能的影响  

Influence on the performance of compressor cascade with alterative incidence angles by the plasma

作　　者：刘华坪[1] 陈焕龙[1] 袁继来[1] 陈浮[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《航空动力学报》2011年第8期1871-1878,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(50976026)

摘　　要：进行了不同冲角、不同电压以及不同电极安装位置下等离子体对大折转角扩压叶栅性能的影响研究.结果表明,当冲角增大时,分离流动加剧是叶栅损失增加的主要原因,而端壁附面层内的摩擦损失则由于流向速度的减小反而减少;等离子体在三种工况下(i=0°,5°,-5°)均可有效控制栅内流动分离、减小叶栅损失、增加叶片负荷,电压越大、电极安装位置越接近分离起始位置,其控制效果越明显;随着冲角的增加,等离子体减小能量损失的效果减弱;虽然电极沿整个叶高方向布置,但等离子体仅对约10%叶高以上的损失影响较为明显,同一电压下该范围内各叶高处的损失减小量也基本相同.The plasma effect on the performance of high-turning compressor cascade was investigated at different incidence angles, voltages and electrodes locations. The results show that, with the increase of the incidence angle, the aggravation of the flow separation is a primary reason for the increase of the cascade losses, while the boundary layer losses near the end-wall decrease due to the reduction of the flow velocity. At all the incidence an- gles （i=0°, 5°, -5°）, the plasma actuator could weaken the separation, reduce the cas cade losses and increase the blade loading effectively. The bigger the voltage and the closer the electrodes to the separation line, the more obvious the plasma effect becomes. And the bigger incidence angle leads to weaker plasma effect. Although the electrodes are installed along the whole blade height, the plasma merely reduces the losses in the region above 10° blade height, and the loss reduction is almost the same in this zone.

关 键 词：等离子体 扩压叶栅 附面层 流动控制 叶栅损失 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]