端壁抽吸位置对大转角扩压叶栅流场及负荷的影响  

Effects of endwall boundary layer suction position on the flow field and load in a high-turning compressor cascade

作　　者：郭爽[1] 陈浮[1] 陆华伟[2] 陈绍文[1] 宋宇飞 宋彦萍[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001 [2]大连海事大学轮机工程学院,辽宁大连116026 [3]深圳中广核工程有限公司,广东深圳518049

出　　处：《推进技术》2011年第3期323-328,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金项目(50976026)

摘　　要：实验研究了低速条件下在端壁近吸力面处进行附面层吸除对某大转角扩压叶栅性能的影响。对叶栅出口截面参数和叶片型面静压进行了测量,并在叶片表面及端壁进行了墨迹流动显示。结果表明,端壁抽吸主要影响了吸力面/端壁角区,重新分配叶片根部负荷。在角区未发生分离的位置开始抽吸可有效推迟叶栅内的角区分离,降低损失,改善叶栅端区流动;而在角区已经发生分离的弦向位置开槽吸气则引起了局部回流,恶化了流场,增加了低能流体的掺混和气动损失。Experimental investigation was carried out to study the effects of the boundary layer suction implemented close to the suction surface on the endwall on improving the aerodynamic performance of a compressor cascade with a large camber angle.The flow fields of the cascade and the static pressure by tapping on the cascade surfaces were measured,and the ink-trace flow visualization was also conducted.Experimental results show that the applied manner of boundary layer suction mainly affects the suction and endwall corner region and the load of the blade root redistribution after suction.Suction before the separation in endwall corner region happening delays the flow separation,decreases cascade losses,and improves the flow condition of the endwall region effectively.But suction after the separation has occurred even worsens the flow field and enhances the blending of the low energy fluid,and increases losses.

关 键 词：端壁吸气+ 吸气位置+ 大转角扩压叶栅 实验研究 

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]