IMPROVED DESIGN AND ANALYSIS OF A CENTRIFUGAL COMPRESSOR WITH LARGE ATTACK ANGLE
In order to improve the performance of a centrifugal compressor in an air turbine expander, the impeller of it was improved in this paper. Considering to improve efficiency of the impeller and reduce difficulty in producing it, and in order to compare the difference of the flow conditions between impellers with different inlet angles, three impellers with inlet angles 43°,50°, 56° were designed in this paper, and their attack angles were 15°, 8°, 2° at the design point. The newly designed impellers were only changed the inlet angles while their other parameters were same to the original impeller. Numerical simulation of the four compressors were made by using Reynold averaged Navier-Stokes equations, and their characteristic lines were calculated in this paper. Especially the flow fields inside the impellers were analyzed in detail. The analysis shows that there are terrible separate flows in the original impeller and as the inlet angle increases the flow conditions are improved. It is concluded that the efficiencies, the pressure ratios and the stability ranges of the three newly designed impellers are all increased and the impeller with 56° inlet angle has the highest efficiency and pressure ratio.
centrifugal compressor inlet angle flow analysis improved design
ZHENG Hua FANG Xiang-jun WANG Ping LIU Si-yong
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
国际会议
昆明
英文
474-477
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）