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Numerical Analysis of High-Altitude Inlet Air on Boundary Layer Flow Loss in an Aero-Engine Compressor

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  • Feng Wu

    (School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China
    Science and Technology on Altitude Simulation Laboratory, AECC Sichuan Gas Turbine Establishment, Mianyang 621000, China)

  • Limin Gao

    (School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China)

  • Lu Yang

    (College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China)

  • Aqiang Lin

    (School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China)

  • Hai Zhang

    (College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China)

Abstract

A numerical analysis is performed to explore the high altitude and high Mach flight on the effect of wall boundary layer loss in the compressor. The accuracy for solution results by the application of the similarity criterion and parameter definition of the air inlet is compared with the existing experimental test result. The results indicate that the radial adverse pressure gradient in the rotor domain gradually increases along the span direction and decreases as flight Mach number increases; meanwhile, the circumferential adverse pressure gradient on the pressure side of the rotor blade is correspondingly larger and less than that on the suction side. In particular, the entropy increase along the streamwise shows a decreasing trend and an increasing trend inside the hub and shroud wall boundary layers, respectively. At 2.1 Ma , the entropy increase in the rotor domains enhances by 24.36–27.80% inside the shroud boundary layer, relative to the hub boundary layer; however, it decreases by 0.97–8.54% in the stator domain. With the increase in flight Mach number from 2.1 to 3.4, the average entropy increase reductions in the rotor domain decrease by 18.99–24.97% within the hub boundary layer and 5.71–8.1% within the shroud boundary layer. In the stator domain, it drops by 18.45–9.03% inside the hub boundary layer and 6.88–8.67% inside the shroud boundary layer. It was therefore found that, as Mach number increases from 2.1 to 3.4, the entropy increase reduction is larger inside the hub boundary layer than inside the shroud boundary layer.

Suggested Citation

  • Feng Wu & Limin Gao & Lu Yang & Aqiang Lin & Hai Zhang, 2020. "Numerical Analysis of High-Altitude Inlet Air on Boundary Layer Flow Loss in an Aero-Engine Compressor," Energies, MDPI, vol. 13(16), pages 1-14, August.
    • Handle: RePEc:gam:jeners:v:13:y:2020:i:16:p:4155-:d:397625
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    References listed on IDEAS

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    1. Wenfeng Zhao & Qun Zheng & Bin Jiang & Aqiang Lin, 2020. "A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions," Energies, MDPI, vol. 13(11), pages 1-17, May.
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