Experiments of effects of inlet-air distortion on aerodynamic performance in transonic compressor

作     者：LI Mao-yi YUAN Wei LU Ya-jun SONG Xi-zhen LU Li-peng 

作者机构：National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamicsSchool of Energy and Power EngineeringBeijing University of Aeronautics and Astronautics 

出 版 物：《航空动力学报》 (Journal of Aerospace Power)

年 卷 期：2013年第28卷第5期

页      面：1047-1056页

核心收录：

学科分类：082502[工学-航空宇航推进理论与工程] 08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：National Natural Science Foundation of China(50906001) 

主　　题：plugboard simulator inlet-air distortion transonic axial-flow compressor shock wave disturbance 

摘      要：The inlet-air distortion which was caused by high angle-of-attack flight was simulated by *** were conducted on a transonic axial-flow compressor s rotor at 98% rotating *** flow-field characteristics and mechanism of performance degradation were analyzed in *** compressor inlet was divided into four sectors at circumference under inlet-air *** were undistorted sector,transition sector A where the rotor was rotating into the distortion sector,distorted sector and transition sector B where the rotor was rotating out of the distortion *** experimental results show that compared with undistorted sector,there is a subsonic flow in transition sector A,so the pressure ratio is decreased by a large margin in this ***,the shock wave is enhanced in distortion sector and transition sector B,and thus the pressure ratio increases in these *** of the different works at circumference,the phase angle of total pressure changes 90° when the inlet total pressure distortion passes through compressor *** addition,the frequency and amplitude of disturbances in front of the rotor strengthenes under inlet distortion,so the unstable flow would take place in *** addition,the position of stall inception is in one of the transition sectors.