Abstract: In order to study the effects of the tip leakage flow on the aerodynamic performance of a small as.pect-ratio highly-loaded transonic rotor，numerical simulation is carried out for analysis of the all operating con.ditions and flow structures near the tip at different tip gap in detail. The results show that，under the condition of zero tip gap，the rotor has the highest peak efficiency while the narrowest working range. The existence of leak.age flow could suppress the development of the corner separation in the flow passage，which helps to delay thetriggering of stall and raise the rotor stall margin by 20%. The tip leakage vortex is broken down after interactingwith the shock wave at a higher tip gap，however，adoption of the low-reaction design idea could control the bro.ken vortex not to spread in a large extend. This could guarantee a higher efficiency for the rotor even at near stallcondition. Taking all the aerodynamic aspects into consideration， for this kind of rotor， an optimal tip gap should be existed.

Key words: Highly-loaded compressor；Low reaction；Tip leakage flow；Shock wave

摘要： 为探究叶顶泄漏流动对小展弦比高负荷跨声速转子气动性能的影响，利用数值模拟的手段，对不同尺度叶顶间隙下低反动度转子的全工况特性以及叶顶区域的流场结构进行了详细分析。研究结果表明，无叶顶间隙条件下，转子峰值效率最高，但其工作范围较窄；叶顶泄漏流动可在一定程度上抑制角区分离流动在流道内部的发展，延缓失速的触发，转子喘振裕度提升 20%以上；较大尺度叶顶间隙下，波涡干涉导致叶顶泄漏涡破碎，但采用低反动度设计理念可控制破碎的泄漏涡在流道内部不发生大尺度的扩散，从而进一步地保证了转子在近失速点处仍具有较高的效率；综合考虑多方面气动性能要求，对于此类转子应存在最佳的叶顶间隙值。

关键词: 高负荷压气机；低反动度；叶顶泄漏流；激波