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Numerical simulation of three-dimensional turbulent flow in multistage axial compressor blade row

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Abstract

Numerical simulation of three-dimensional turbulent flow in a multistage axial compressor blade row is conducted. A high resolution, third-order ENN scheme is adopted to catch the shockwave and simulate the turbulent flow correctly, while an LU-SGS implicit method is chosen to improve computation rate. A detailed and highly efficient numerical simulation system is thus constructed. The investigation is focused on the grid connecting methods between the rotor and the stator and the corresponding treatment of rotor-stator interactional surface. The final results of a three-stage axial compressor with inlet guide vanes conform well to the experimental data.

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Authors and Affiliations

  1. Engine Department of Chinese Flight Test Establishment, Xi’an, 710089, China

    Jian Jiang

  2. National Key Laboratory of Airfoil and Cascade Aero-Dynamics, Northwestern Polytechnical University, Xi’an, 710072, China

    Bo Liu, Yangang Wang & Xiangyi Nan

Authors
  1. Jian Jiang
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  2. Bo Liu
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  3. Yangang Wang
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  4. Xiangyi Nan
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Corresponding author

Correspondence to Jian Jiang.

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Translated from Chinese Journal of Applied Mechanics, 2007, 24(1): 21–25 [译自: 应用力学学报]

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Jiang, J., Liu, B., Wang, Y. et al. Numerical simulation of three-dimensional turbulent flow in multistage axial compressor blade row. Front. Energy Power Eng. China 2, 320–325 (2008). https://doi.org/10.1007/s11708-008-0041-2

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  • DOI: https://doi.org/10.1007/s11708-008-0041-2

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