前缘侵蚀对风扇转子叶片气动特性的影响机理

doi:10.7527/S1000-6893.2019.23007

Abstract

Abstract: In this paper, a small large bypass ratio turbofan engine fan rotor is taken as the research target. The aerodynamic characteristics decay of the aero-engine fan rotor blades during the flight process are numerically studied, laying a theoretical foundation for the subsequent refined maintenance. After the fan rotor blade is eroded, the leading-edge of the blade will gradually become blunt-headed with pronounced surface roughness. To simplify the research, this paper assumes that the roughness of the leading-edge of the rotor blade after erosion is evenly distributed, and the rotor characteristics of the leading-edge roughness with 120 μm and 250 μm are calculated. The results show that the peak efficiency of the fan rotor is reduced by 1.63% and 2.39% compared with the prototype blade. When the leading-edge roughness is 250 μm, there is a separation trace on the near-wall limit streamlines of the front edge of the fan rotor blade suction, and the average Mach number of the outlet decreases by 2.03%.

Key words: fan rotor, leading-edge erosion, chord length change, roughness, performance degradation

CLC Number:

V231.3

SHI Lei, YANG Guang, LIN Wenjun. Influence mechanism of leading-edge erosion on aerodynamic performance of fan rotor blade[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 123007-123007.

References 20

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Influence mechanism of leading-edge erosion on aerodynamic performance of fan rotor blade

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