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An aerodynamic design and numerical investigation of transonic centrifugal compressor stage

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Abstract

In the present paper, the design of a transonic centrifugal compressor stage with the inlet relative Mach number about 1.3 and detailed flow field investigation by three-dimensional CFD are described. Firstly the CFD program was validated by an experimental case. Then the preliminary aerodynamic design of stage completed through in-house one-dimensional code. Three types of impellers and two sets of stages were computed and analyzed. It can be found that the swept shape of leading edge has prominent influence on the performance and can enlarge the flow range. Similarly, the performance of the stage with swept impeller is better than others. The total pressure ratio and adiabatic efficiency of final geometry achieve 7:1 and 80% respectively. The vane diffuser with same airfoils along span increases attack angle at higher span, and the local flow structure and performance is deteriorated.

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Authors and Affiliations

  1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing, 100081, China

    Lucheng Ji

  2. Research Center for Energy and Power, Chinese Academy of Sciences, Beijing, 100190, China

    Weilin Yi, Yong Tian, Weiwei Shao, Weiwei Li & Yunhan Xiao

  3. Key Laboratory of Advanced Energy and Power, Chinese Academy of Sciences (Institute of Engineering Thermophysics), Beijing, 100190, China

    Weilin Yi, Yong Tian, Weiwei Shao, Weiwei Li & Yunhan Xiao

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  1. Weilin Yi
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  2. Lucheng Ji
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  3. Yong Tian
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  4. Weiwei Shao
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  5. Weiwei Li
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  6. Yunhan Xiao
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Yi, W., Ji, L., Tian, Y. et al. An aerodynamic design and numerical investigation of transonic centrifugal compressor stage. J. Therm. Sci. 20, 211–217 (2011). https://doi.org/10.1007/s11630-011-0460-y

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  • DOI: https://doi.org/10.1007/s11630-011-0460-y

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