端壁附面层抽吸对大转角扩压叶栅旋涡影响的实验研究  

Experimental Investigation on Effects of Endwall Boundary Layer Suction on Vortexes of High-Turning Compressor Cascades

作　　者：郭爽[1] 陆华伟[2] 宋彦萍[3] 吴锤结[1] 

机构地区：[1]大连理工大学航空航天学院/工业装备结构分析国家重点实验室,辽宁大连116024 [2]大连海事大学轮机学院,辽宁大连116026 [3]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2013年第11期1466-1473,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(51206013);辽宁省博士启动基金(20131020);中国博士后科学基金(2013M540223)

摘　　要：为探明附面层抽吸技术对压气机叶栅气动性能的影响及其与栅内旋涡结构的关联,通过十个横截面的实验测量结果研究了高负荷压气机叶栅抽吸端壁附面层前后的主要旋涡结构以其对应损失的演变过程。研究对象为矩形低速扩压叶栅,来流马赫数约为0.23。研究结果表明,端壁附面层的变化对叶栅端区的主要旋涡发展过程影响显著。在原型方案中,壁面涡、尾缘脱落涡的演变过程对应着较高的流动损失,通道涡自身产生的损失较小,主要起到向远离端壁的方向输运低能流体的作用;在流向槽吸气方案中,壁面涡和尾缘脱落涡因端壁附面层径向迁移及角区分离受到抑制而被明显削弱;而来流附面层抽吸方案则最为有效地控制了通道涡的演变过程。This paper presents results of experimental investigations carried out to explore the effects of endwall boundary layer suction on principal vortices and the performance of high-turning compressor cas- cades. Section measurements were conducted at ten different axial positions distributed from upstream to downstream of the rectangular cascade. The inlet Mach number is about 0.23. Experimental results demon- strate that the evolution of majority vortices in the endwall region is sensitive to the variation of endwall boundary layer. The wall vortex and the trailing edge vortex contribute much in cascade losses, while the passage vortex which transfers low energy fluid away from the endwall only produces a small amount of loss in the original scheme. The shedding vortex is obviously suppressed in the streamwise suction slot schemes as both the secondary transition of endwall boundary layer and corner region separation are under control.The development of passage vortex is most effectively controlled in the suction scheme which transfers part of inlet boundary layer away from the cascade.

关 键 词：大转角扩压叶栅 附面层抽吸 二次流动 旋涡结构 流动损失 抽吸位置 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]