Abstract: Unsteady flow field of transonic compressor NASA Rotor67 was analyzed under the assumption of rigid blade，and then two-way fluid-structure interaction (FSI) numerical method was used to analyze the effects of aero-elasticity on the tip clearance flow field under near stall condition. Through the comparisons between flow fields of rigid blade and flexible blade，unsteady characteristics of macro property of the flow fields were investigated，and the effects of aero-elasticity on the fluctuation frequency of macro property，the starting point of boundary layer separation at tip clearance and the shedding frequency of trailing edge vortex were also analyzed. Moreover，emphasis was given to the effect of aero-elasticity on the trajectory，fluctuation frequency and influence scope of tip clearance leakage vortex. Results shows that the effects of aero-elasticity increases，the fluctuation frequency of macro property and leakage vortex by 33.2% and 2.28%，respectively，while decreases the fluctuation frequency of boundary layer separation and shedding vortex at trailing edge by 5.75% and 0.75%，respectively. Also，it moves forward the starting point of separation at tip of blade.

Key words: Transonic compressor；Aero-elastic effects；Near stall condition；Tip leakage flow

摘要： 以NASA Rotor 67跨声速压气机转子为研究对象，在刚性叶片条件下进行了内流场非定常流动分析，并以此为基础，应用双向流固耦合(FSI)方法分析了该压气机在近失速点工况下气弹效应对叶顶间隙区流场的影响。通过对比分析，研究了刚性叶片与柔性叶片条件下该压气机的宏观非定常波动特征，分析了气弹效应对宏观性能波动频率、叶尖附面层分离起始点与尾缘涡脱落频率的影响，给出了叶片振动对前缘处宏观性能波动频率的影响大于尾缘处的原因。研究了气弹效应对叶顶间隙泄漏涡运动轨迹、波动频率以及作用范围的影响。结果显示，气弹效应使得尾缘处宏观性能以及泄露涡的波动频率分别增大了33.2%、2.28%，叶尖附面层分离涡与尾缘脱落涡的波动频率分别降低5.75%、0.75%，同时使得叶尖附面层分离起始点前移。

关键词: 跨声速压气机；气弹效应；近失速工况；叶顶泄漏流