Numerical Investigation of a Centrifugal Compressor with a Pre-Compression Wedge Diffuser under High Subsonic Conditions  

作　　者：WANG Yi LI Qingkuo BAI Huan ZHOU Xueqi LU Xin’gen 

机构地区：[1]School of Aeronautics and Astronautics,Central South University,Changsha 410083,China [2]AECC Hunan Aviation Powerplant Research Institute,Hunan Key Laboratory of Turbomachinery on Small and Medium Areo-Engine,Zhuzhou 412002,China [3]Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China

出　　处：《Journal of Thermal Science》2020年第4期945-954,共10页热科学学报（英文版）

摘　　要：As the total pressure ratio of centrifugal compressors increases, the diffuser inlet flow becomes highly subsonic or even supersonic, which causes additional shock loss. The shock loss leads the stage performance to drop greatly. Pre-compression is an efficient method for reducing shock loss and improving the stage performance. To study the effect of wedge diffusers with pre-compression blades on centrifugal compressor performance, wedge diffusers with various pre-compression angles, divergence angles and numbers of blades were designed and investigated via a numerical method. As a result, it is found that the compressor stage achieves high peak efficiency when the pre-compression angle ranges from 2.5° to 5.5° and when the divergence angle ranges from 7° to 9°. As the number of blades increases, the total pressure ratio and adiabatic efficiency of the compressor stage increase slightly, whereas the surge margin of the stage decreases.

关 键 词：wedge diffuser pre-compression high Subsonic centrifugal compressor 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]