纳秒脉冲等离子体激励控制低雷诺数压气机叶栅激波/附面层干扰探索研究  

Research on Shock Wave/Boundary Layer Interference Control in the Supersonic Compressor Cascade Using Plasma Actuation at Low Reynolds Number

作　　者：汪一舟 张海灯 吴云[1,2] 李应红[1] 盛佳明 WANG Yizhou;ZHANG Haideng;WU Yun;LI Yinghong;SHENG Jiaming(Science and Technology on Plasma Dynamics Laboratory,Aeronautics Engineering College,Air Force Engineering University,Xi'an 710038,China;School of Mechanical Engineering,Xi'an Jiaotong University,Xi'an 7710049,China)

机构地区：[1]空军工程大学航空工程学院等离子体动力学重点实验室,西安710038 [2]西安交通大学机械学院,西安710048

出　　处：《工程热物理学报》2023年第4期903-913,共11页Journal of Engineering Thermophysics

基　　金：国家自然科学基金(No.51906254,No.51790511);重点实验室基金(No.614220119040510);国家科技重大专项(No.2019-I-0011);国家科技重大专项(No.2017-II-0005)。

摘　　要：为了揭示等离子体激励调控低雷诺数压气机叶栅激波/附面层干扰的机理,本文选取典型超音速压气机预压缩叶型,利用大涡模拟研究了纳秒脉冲等离子体激励对低雷诺数下超音速压气机叶型附面层流动的调控作用。首先对低雷诺数工况下超音速压气机叶型流动特性和叶栅通道激波系结构进行了研究,以此设计了两种等离子体激励布局。研究发现,位于叶片吸力面和压力面附面层分离点前的等离子体激励均可通过诱导产生畸变团,触发分离剪切层的K-H不稳定并进一步形成展向大涡结构,促进主流与分离区低能流体之间的掺混从而抑制流动分离。同时叶栅通道激波系结构发生改变,分离区形态与通道激波位置相互关联耦合,附面层黏性损失和激波损失占比变化不尽相同。In order to reveal the control mechanism of shock wave/boundary layer interaction in the supersonic compressor cascade at low Reynolds number using plasma actuation,large eddy simulation(LES)is used to study the effects of nanosecond pulse plasma actuation on the boundary layer flow of the supersonic compressor airfoil at low Reynolds number.Flow characteristics of the supersonic compressor airfoil and shock wave systems of the cascade passage under low Reynolds number are studied firstly,then two kinds of plasma actuation layouts are designed.It is found that the plasma actuation imposed in front of the boundary layer separation point of the blade suction surface and pressure surface both can induce the distorted fow structure.The distorted fow structure can trigger the K-H instability of the separated shear layer and induce the spanwise large vortex structure,which can suppress fow separation through promoting the mixing between the main fow and the low-energy fluid in the separation zone.Meanwhile,the shock wave system has been changed due to plasma actuation.It has been found that the shape of separation zones is associated with the position of passage shock waves,which causes various changes of the ratio of boundary layer viscous loss and shock loss.

关 键 词：压气机叶栅 附面层 激波 等离子体激励 流动控制 

分 类 号：V211.6[航空宇航科学与技术—航空宇航推进理论与工程]