摘 要：随着航空发动机的推重比和耗油率等要求不断严苛，高负荷压气机的设计成功与否直接决定着发动机能否换代升级。为研究高负荷轴流压气机的转子叶型参数对于其性能的影响，本文基于一款高负荷轴流压气机作为研究对象，通过参数化建模和数值仿真方法系统研究了该高负荷压气机的转子叶片弯、掠度和前、尾缘椭圆度等关键叶型参数对其稳定裕度、压比和效率等性能参数的影响情况。发现前缘椭圆度较小的转子叶片可显著提高该高负荷压气机的压比、最高效率和稳定裕度，而尾缘椭圆度对此影响不够明显。弯、掠度都会影响该高负荷压气机的稳定裕度，但是朝着出口方向的掠程度不宜太大，否则会导致严重的稳定裕度损失，为建立标准规范的高负荷压气机设计准则提供仿真数据支持。
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.
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