Experimental Research on Inlet Steady Swirl Distortion in an Axial Compressor with Non-Uniform Tip Clearance  

作　　者：XU Rong HU Jun WANG Xuegao JIANG Chao LI Wenyu 

机构地区：[1]College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

出　　处：《Journal of Thermal Science》2023年第1期286-296,共11页热科学学报（英文版）

基　　金：supported by National Science and Technology Major Project(Grant No.2017-II-0004-0017)。

摘　　要：The inlet swirl distortion and non-uniform tip clearance have great effects on aero-engine performance and stall margin.In this paper,the effects of paired swirl distortion on the aerodynamic stability and stall inception of a single stage axial compressor with non-uniform tip clearance are quantitatively analyzed by using the swirl distortion descriptors.The experimental results show that the paired swirl distortion dominated by co-rotating swirl improves the stability of the axial compressor.For a single-stage axial compressor with eccentricity of 100%,the stall inception starts at the maximum tip clearance with clean inlet.The initial position of the stall inception is determined by the maximum tip clearance when the small intensity paired swirl distortion exists at the compressor inlet.As the swirl intensity increases,it shifts towards the position of the counter rotating swirl vortex core.The inlet swirl will not change the type of stall inception.

关 键 词：steady swirl distortion non-uniform tip clearance stall inception experiment research compressor performance 

分 类 号：TH45[机械工程—机械制造及自动化]