Progressing advancement concerning the intensification of engine thrust to weight ratio in a gas turbine engine offers ascends to extremely loaded compressor stages which have a significant concern in recent times. Non-uniform Inlet flow conditions are frequently occurring in aircraft gas turbines engines that result in chronological distortions of total temperature and total pressure at the engine inlet. Distorted inlet flow operation of the axial compressor deteriorates the aerodynamic performance which reduces stall margin and increased blade stress levels. The current paper aims at the investigation of the flow field in the tip clearance region of the transonic micro-axial flow compressor at non-uniform flow conditions. Under the design and off-design RPM, the current paper focuses on the adverse effects of a steady-state distorted pattern of total pressure inlet flow conditions, including hub radial, tip radial pressure distortion, and combined effects of pressure distortion with bulk swirl flow to evaluate its effects on compressor performance and stability. The results show that like hub radial pressure distortion improves the stability range of turbofan transonic micro-compressor rotor. Whereas tip radial and counter swirl flow deteriorate the performance of the compressor. Furthermore, compressor performance alleviated the stall at higher RPM combined with distorted inlet pressure.

关于在燃气涡轮发动机中发动机推力与重量比的增强的进步使得上升到极端负荷的压缩机级，这是近来备受关注的问题。飞机燃气涡轮发动机中经常发生进气口流量不均匀的情况，这会导致发动机进口处的总温度和总压力按时间顺序发生变化。轴向压缩机的进气流操作失真会降低空气动力学性能，从而降低失速裕度并增加叶片应力水平。本文旨在研究非均匀流动条件下跨音速微轴流压气机尖端间隙区域内的流场。在设计和非设计的RPM下，当前的论文集中在总压力入口流量状况的稳态畸变模式的不利影响，包括轮毂径向，尖端径向压力畸变以及压力畸变与大涡旋流的组合影响，以评估其对压缩机性能和稳定性的影响。 。结果表明，类似轮毂的径向压力畸变改善了涡扇式跨音速微型压缩机转子的稳定性范围。而尖端的径向和逆向旋流会降低压缩机的性能。此外，压缩机的性能减轻了转速较高时的失速现象，同时入口压力变形。以及压力畸变与整体涡流的综合作用，以评估其对压缩机性能和稳定性的影响。结果表明，类似轮毂的径向压力畸变改善了涡扇式跨音速微型压缩机转子的稳定性范围。而尖端的径向和逆向旋流会降低压缩机的性能。此外，压缩机的性能减轻了转速较高时的失速现象，同时入口压力变形。以及压力畸变与整体涡流的综合作用，以评估其对压缩机性能和稳定性的影响。结果表明，类似轮毂的径向压力畸变改善了涡扇式跨音速微型压缩机转子的稳定性范围。而尖端的径向和逆向旋流会降低压缩机的性能。此外，压缩机的性能减轻了转速较高时的失速现象，同时入口压力变形。