跨声速风扇转子叶片在实际运行中会遭受前缘侵蚀等形貌衰变问题，端区流场结构会发生变化进而诱发气动性能衰退，采用定常数值计算方法探究前缘侵蚀对风扇转子叶尖泄漏流动的影响。结果表明，在侵蚀叶片失速点，其等熵效率、总压比和质量流量分别相对下降4.3%、0.43%和5.63%，还会造成稳定工作裕度降低了0.74%；对于端区内的流动，前缘侵蚀会在间隙处S1流面和出口区域S3流面引起熵增面积和强度的增加，在不同叶高下形成低马赫数流动区域；泄漏流结构在前缘侵蚀下发生恶性变化，主泄漏流和次泄漏流的分界点提前，携带有更多的流体发生二次泄漏，侵蚀叶片的泄漏涡偏转角度由15°达到30°，直接打在叶片前缘，造成流动堵塞。

Transonic fan rotor blades will suffer from morphological decay problems such as leading edge erosion in actual operation, and the flow field structure in the tip zone will change and then induce aerodynamic performance degradation. The effects of leading edge erosion on the tip leakage flow of the fan rotor were investigated from constant numerical computation in this paper. The results show that at the stall point of the eroded blade, its isentropic efficiency, total pressure ratio and mass flow rate decrease by 4.3%, 0.43% and 5.63%, respectively, and the leading-edge erosion also causes a decrease in the stabilized operating margin by 0.69%. For the flow in the tip zone, the leading-edge erosion causes an increase in the entropy increase area and intensity in the flow surface of S1 at the tip zone and the flow surface of S3 in the exit region, and the formation of a low Mach Number flow region in different blade heights; the leakage flow structure under the leading edge erosion undergoes malignant changes, the demarcation point of the main leakage flow and the secondary leakage flow is advanced, carrying more fluid for secondary leakage, and the leakage vortex deflection angle of the eroded blade reaches 30° from 15°, hitting the leading edge of the blade directly and causing flow blockage.