Abstract: In this study, the effect of the inlet angle of a centrifugal impeller blade on the aerodynamic performance of a centrifugal compressor was investigated. Five groups of impeller bending angles and three groups of blade root inclination angles at the blade inlet of the centrifugal impeller were designed to obtain different blade inlet angles of the impeller. The computational fluid dynamics method was used to simulate and analyze the flow fields of centrifugal compressors with different blade shapes under design conditions. The results show that for transonic microcentrifugal compressors, an increase in the inlet blade tip bending angle increases the isentropic efficiency and pressure ratio of the compressor. When the blade tip bending angle increases from 50° to 70°, the pressure ratio of the centrifugal compressor increases by 17%, the isentropic efficiency increases by 22%, the inlet airflow angle decreases, and the outlet airflow angle increases. Increasing the blade root inclination angle decreases the compressor outlet pressure ratio by 2.4% and the isentropic efficiency by 3.9%. The blade inlet bending angle is a critical parameter for increasing the isentropic efficiency and pressure ratio. This proposed analysis method provides a reference for rationally selecting the blade leading edge angle and designing transonic microcentrifugal compressors.
徐玉东, 陈宏博, 霍莹. 微型离心叶轮叶片进口角度对压气机性能影响[J]. 吉林化工学院学报, 2024, 41(5): 79-87.
Xu Yudong, Chen Hongbo, Huo Ying . Effect of Inlet angle of Minicentrifugal Impeller Blade on Performance of Centrifugal Compressor. Journal of Jilin Institute of Chemical Technology, 2024, 41(5): 79-87.
