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Corner Separation Control by Boundary Layer Suction Applied to a Highly Loaded Axial Compressor Cascade

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Listed:
  • Yangwei Liu

    (National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy and Power Engineering, Beihang University, Xueyuan Road 37, Haidian District, Beijing 100191, China
    Collaborative Innovation Center of Advanced Aero-Engines, Xueyuan Road 37, Haidian District, Beijing 100191, China)

  • Jinjing Sun

    (National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy and Power Engineering, Beihang University, Xueyuan Road 37, Haidian District, Beijing 100191, China
    Collaborative Innovation Center of Advanced Aero-Engines, Xueyuan Road 37, Haidian District, Beijing 100191, China)

  • Lipeng Lu

    (National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy and Power Engineering, Beihang University, Xueyuan Road 37, Haidian District, Beijing 100191, China
    Collaborative Innovation Center of Advanced Aero-Engines, Xueyuan Road 37, Haidian District, Beijing 100191, China)

Abstract

Control of corner separation has attracted much interest due to its improvement of performance and energy utilization in turbomachinery. Numerical studies have been performed under both design and off-design flow conditions to investigate the effects of boundary layer suction (BLS) on corner separation in a highly loaded compressor cascade. Two new BLS slot configurations are proposed and a total of five suction slot configurations were studied and compared. Averaged static pressure rise, exit loss coefficient, passage blockage and flow turning angle have been given and compared systematically over a range of operation incidence angles. Distributions of significant loss removal, blade loading, exit deviation and total pressure loss at 3 degree and 7 degree incidence have also been studied. Under the same suction mass flows of 0.7% of the inlet mass flows, the pitchwise suction slot on the endwall shows a better optimal performance over the whole operation incidence among single suction slots. By using of the new proposed compound slot configuration with one spanwise slot on the blade suction side and one pitchwise slot on the endwall, the maximum reduction of total pressure loss at 7 degree incidence can be 39.4%.

Suggested Citation

  • Yangwei Liu & Jinjing Sun & Lipeng Lu, 2014. "Corner Separation Control by Boundary Layer Suction Applied to a Highly Loaded Axial Compressor Cascade," Energies, MDPI, vol. 7(12), pages 1-14, November.
    • Handle: RePEc:gam:jeners:v:7:y:2014:i:12:p:7994-8007:d:42831
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    Cited by:

    1. Yumeng Tang & Yangwei Liu, 2020. "Aerodynamic Investigation of Datum and Slotted Blade Profiles under Different Mach Number Conditions," Energies, MDPI, vol. 13(7), pages 1-22, April.

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