Influence of sub boundary layer vortex generator height and attack angle on cross-flows in the hub region of compressors  

作　　者：Hao FU Ling ZHOU Lucheng JI 

机构地区：[1]School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China [2]Institute for Aero Engine,Tsinghua University,Beijing 100084,China

出　　处：《Chinese Journal of Aeronautics》2022年第8期30-44,共15页中国航空学报（英文版）

基　　金：sponsored by the National Natural Science Foundation of China(Nos.51976010,52006011);National Major Science and Technology Projects of China(Nos.2017Ⅱ-0006-0020,2017-Ⅱ-0001-0013,J2019-Ⅱ-0003-0023);Beijing Institute of Technology Research Fund Program for Young Scholars,China。

摘　　要：It has been recently shown that Sub Boundary layer Vortex Generator(SBVG,abbreviated as VG hereafter)can suppress the Cross-Flow(CF),and therefore,can eliminate corner separation and increase aerodynamic loading when installed on the end wall inside middle-load compressor passages.However,when VGs are applied in high-load compressors,it is difficult to achieve ideal results.This is because the definition of the VG attack angle in the presence of CF in existing research is confusing,and the stronger CF in high-load compressors worsens the problem and results in an improper design and optimization range of VG attack angle.Therefore,this paper clarifies the definition of the VG attack angle in the presence of CF and reveals the CF controlling mechanism of VG on a flat plate.The differences in the flow phenomena around a VG both with and without CF are also studied.The numerical results show that a larger height or attack angle of the VG generates a greater CF suppression effect.However,the cross velocity increases when surmounting the primary vortex induced by the VG,except that this enhanced CF is less conspicuous for larger VG heights.Compared to the cases without CF,the VG suffers an additional loss because of the stronger separation and primary vortex loss caused by the CF.

关 键 词：Compressors Corner separation CROSS-FLOW Flat plate Vortex generator 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]