Affiliations: [a] College of Mechanical and Electric Engineering, Changchun University of Science and Technology, Changchun, China | [b] Engineering Training Centre, Jilin Institute of Chemical Technology, Jilin, China | [c] AVIC Aerodynamics Research Institute, Harbin, China
Correspondence:
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Corresponding authors: Xu Yu Dong, Changchun University of Science and Technology, China; and Jilin Institute of Chemical Technology, China. E-mail: [email protected]. Zhang Xin Ming, Changchun University of Science and Technology, China. E-mail: [email protected]
Abstract: In order to study the effect of the trailing edge sweep angle of the centrifugal impeller on the aerodynamic performance of the centrifugal compressor, 6 groups of centrifugal impellers with different bending angles and 5 groups of different inclination angles were designed to achieve different impeller blade trailing edge angle. The computational fluid dynamics (CFD) method was used to simulate and analyze the flow field of centrifugal compressors with different blade shapes under design conditions. The research results show that for transonic micro centrifugal compressors, changing the blade trailing edge sweep angle can improve the compressor’s isentropic efficiency and pressure ratio. The pressure ratio of the compressor shows a trend of increasing first and then decreasing with the increase of the blade bending angle. When the blade bending angle is 45°, the pressure ratio of the centrifugal compressor reaches a maximum of 1.69, and the isentropic efficiency is 67.3%. But changing the inclination angle of the blade trailing edge has little effect on the isentropic efficiency and pressure ratio. The sweep angle of blade trailing edge is an effective method to improve its isentropic efficiency and pressure ratio. This analysis method provides a reference for the rational selection of the blade trailing edge angle, and provides a reference for the design of micro centrifugal compressors under high Reynolds numbers.
