关键词: 关键词：航空发动机, 高负荷压气机, 弯掠度, 椭圆度, 稳定裕度

Abstract: Abstract: With increasingly stringent requirements for thrust-to-weight ratio and fuel consumption rate in aircraft engines, the success of high-loaded compressor design directly determines whether the engine can achieve generational upgrades. To investigate the influence of rotor blade airfoil parameters on the performance of a high-loaded axial compressor, this paper takes a high-loaded axial compressor as the research object. By parametric modeling and numerical simulation methods, the influence of key blade airfoil parameters such as rotor blade lean/sweep and leading/trailing edge ellipticity on performance parameters such as stall margin, pressure ratio, and efficiency of the high-loaded compressor is systematically studied. It was found that rotor blades with smaller leading edge ellipticity can significantly improve the pressure ratio, maximum efficiency, and stall margin of the high-loaded compressor, while the effect of trailing edge ellipticity on this is not significant enough. Leaning and sweeping can both affect the stall margin of the high-loaded compressor, but the sweeping degree in the streamwise direction should not be too large, otherwise it will cause serious stall margin loss. This provides simulation data support for establishing standard specifications for high-loaded compressor design criteria.

Key words: Keywords: aeroengine, high-loaded compressor, lean/sweep, ellipticity, stall margin