组合抽吸对大转角扩压叶栅性能的影响  

Effect of compound boundary layer suction on the performance of a high-load diffusion compressor cascade with a large camber angle

作　　者：郭爽[1] 陈绍文[1] 陆华伟[2] 宋彦萍[1] 陈浮[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,哈尔滨150001 [2]大连海事大学轮机工程学院,大连116026

出　　处：《航空动力学报》2010年第12期2697-2703,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(50976026)

摘　　要：实验研究了低速条件下在端壁和吸力面同时进行附面层吸除对某大转角扩压叶栅性能的影响.在叶片表面及端壁进行了墨迹流动显示,并对叶栅出口截面进行了测量.基于实验的抽吸槽布置方式:端壁吸气主要影响区域是吸力面角区;吸力面抽吸可以减小角区范围,延迟叶片吸力面附面层转捩,改善中径处流场;组合抽吸则优化了叶栅整体流场,使流动更加均一高效,由于削弱了端壁和吸力面附面层间的相互作用,组合抽吸在大吸气量下优于前两种吸气方式.The effect of compound boundary layer suction on the aerodynamic performance of a high-load diffusion compressor cascade with a large camber angle was experimentally investigated through ink-trace flow visualization and outlet flow field measurement.Experimental results show that suction on the endwall mainly influences the suction surface corner;suction on the suction surface not only shrinks the endwall corner region,but also delays the transition of the suction surface boundary layer,and improves the flow field around the midspan;the whole flowfield is improved in the case of compound boundary layer suction,and the performance is superior to each of the former two at high suction flow rates as the interaction between the boundary layer of endwall and suction surface is better controlled.

关 键 词：附面层组合抽吸 大转角扩压叶栅 实验研究 吸气量 吸气位置 

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]