前缘侵蚀对跨声速风扇转子叶片叶尖泄漏流动的影响  

Effects of Leading Edge Erosionof Transonic Fan RotorBlade on Tip Leakage Flow

作　　者：李顶河 王易博 史磊 陈泽桐 姜琪[3] LI Ding-he;WANG Yi-bo;SHI Lei;CHEN Ze-tong;JIANG Qi(Sino-European Institute of Aviation Engineering,Civil Aviation University of China,Tianjin 300300,China;Aeronautical Engineering Institute,Civil Aviation University of China,Tianjin 300300,China;Aircraft Maintenance Engineering Department,Xiamen Airlines Co.,Ltd,Xiamen 361009,China)

机构地区：[1]中国民航大学中欧航空工程师学院,天津300300 [2]中国民航大学航空工程学院,天津300300 [3]厦门航空有限公司飞机维修工程部,厦门361009

出　　处：《科学技术与工程》2025年第11期4786-4792,共7页Science Technology and Engineering

基　　金：民航航空器适航审定技术重点实验室开放基金(SH2022070501)。

摘　　要：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.

关 键 词：前缘侵蚀 跨声速 风扇转子叶片 叶尖泄漏流动 激波 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]