前缘侵蚀对风扇转子叶片气动特性的影响机理

以某小型大涵道比涡扇发动机风扇转子作为研究目标，数值模拟了航空发动机风扇转子叶片在航线运行过程中受到侵蚀效应后的气动特性衰变情况，为后续的精细化维修奠定理论基础。风扇转子叶片侵蚀后，叶片前缘将逐步蜕变为钝头叶型并且伴随有明显的表面粗糙度。为了简化研究，假设侵蚀后的转子叶片前缘粗糙度均匀分布，分别计算了前缘粗糙度为120 μm、250 μm两种前缘侵蚀程度下的风扇转子特性。研究结果表明，风扇转子峰值效率相比于原型叶片依次下降了1.63%和2.39%。当前缘粗糙度为250 μm时，风扇转子叶片吸力面前缘近壁面极限流线有分离迹线产生，出口平均马赫数下降2.03%。

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

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%.