Numerical Research on Inlet Total Pressure Distortion in a Transonic Compressor with Non-Axisymmetric Stator Clearance  

作　　者：XU Wenfeng SUN Peng YANG Guogang HUANG Longsheng FU Wenguang 

机构地区：[1]Marine Engineering College,Dalian Maritime University,Dalian 116026,China [2]College of Airworthiness,Civil Aviation University of China,Tianjin 300300,China

出　　处：《Journal of Thermal Science》2020年第4期893-905,共13页热科学学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(No.51576024,51436002);the Double First Class Construction Special Innovation Project of Dalian Maritime University(No.BSCXXM008)。

摘　　要：Inlet total pressure distortion has great adverse effects on the aero-engine performance. The distorted flow passes through the compressor and becomes non-uniform in the downstream blade rows. Different from previous studies based on the assumption of circumferential uniformity, this study aims to improve circumferential non-uniform flow with the non-axisymmetric structure. Non-axisymmetric stator clearance was adopted to resolve the effects of non-uniform flow caused by inlet total pressure distortion in this paper. The 9 stators with tip clearance were installed in the distorted region and the flow field structure and performance under different operating conditions was studied. The study finds that the non-axisymmetric compressor with 9 tip clearance stators can ensure compressor efficiency while improving compressor stability margin. What’s more, the separation range and strength in the distorted region can be reduced significantly and the anti-distortion capability of compressor can be enhanced.

关 键 词：total pressure distortion non-axisymmetric stator clearance transonic compressor numerical simulation 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]