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Numerical investigation of aerodynamic performance influenced by circumferentially pre-swirling coming flow on the crossover and de-swirling cascade of a multistage centrifugal compressor

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Abstract

Numerical investigation is implemented on aerodynamic performance inside the crossover and de-swirling cascade of a multistage centrifugal compressor. The emphasis is put on the aerodynamic performance influenced by the circumferentially pre-swirling coming flow. The results indicate that flow separation occurs inside the crossover, and the separation area may be changed with different circumferentially pre-swirling coming flow. Decreased pre-swirling intensity of the coming flow may effectively restrain the flow separation and make the outflow from the crossover more uniform, which helps to improve the aerodynamic performance of the successive de-swirling cascade. The flow inside the de-swirling cascade is a non-uniform swirling flow with large separation. The complex secondary flow occurs along the main flow and experiences a process of generating, developing, dissipating and collapsing.

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Authors and Affiliations

  1. College of Power Engineering, University of Shanghai for Science and Technology, Shanghai, 200093, China

    Wang Qikun & Chen Kangmin

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  1. Wang Qikun
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  2. Chen Kangmin
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Correspondence to Wang Qikun.

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Translated from Power Engineering, 2007, 27(1): 24–28, 49 [译自: 动力工程]

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Wang, Q., Chen, K. Numerical investigation of aerodynamic performance influenced by circumferentially pre-swirling coming flow on the crossover and de-swirling cascade of a multistage centrifugal compressor. Front. Energy Power Eng. China 1, 435–440 (2007). https://doi.org/10.1007/s11708-007-0063-5

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  • DOI: https://doi.org/10.1007/s11708-007-0063-5

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