摘要：为揭示高速轴流压气机转子叶片非同步气流激励锁频机理，采用叶片强迫运动的单向流固耦合数值模拟方法研究了1.5级压气机第一级转子叶片不同振动幅值下叶尖非同步气流激励频率特征及全周非定常流场的演化过程。结果表明：转子叶片在2%C和3%C大振幅下出现非同步气流激励频率锁频现象，且非同步气流激励强度随叶片振动幅值增加而增大。一方面，叶片振幅的增加会导致转子叶片气动阻尼下降，大振幅下局部转子叶片面临气弹失稳风险。另一方面，转子叶片高幅值非同步振动会导致压气机的流动稳定性下降，转子叶尖流动分离加剧，其诱发的吸力面径向分离涡是导致叶尖压力剧烈波动的主要原因，压气机流动稳定性和叶片气动弹性稳定性两者在近失速工况下形成相互促进的发展关系。研究结果对多级轴流压气机叶片流致振动失效分析具有重要的指导意义。
Abstract: To reveal the frequency lock-in mechanism of non-synchronous aerodynamic excitation in high-speed axial compressor rotor blades, a one-way fluid-structure interaction numerical simulation method with forced blade motion was employed to investigate the tip non-synchronous aerodynamic excitation frequency and the evolution of the full-annulus unsteady flow fields under different amplitudes of the first rotor blades in a 1.5-stage compressor. The results indicate that a frequency lock-in phenomenon of non-synchronous aerodynamic excitation occurs under large amplitudes of 2%C and 3%C, with the intensity of non-synchronous aerodynamic excitation increasing with the blade amplitude. On one hand, the increase of blade amplitude reduces the aerodynamic damping of the rotor blades, posing a risk of aeroelastic instability for local blades under large amplitudes. On the other hand, the high-amplitude non-synchronous vibration can result in a decrease in compressor flow instability and intensify the tip flow separation，the induced radial separation vortices are identified as the primary cause of severe pressure fluctuations near the tip region. The flow stability of the compressor and the aeroelastic stability of the rotor blades form a mutually reinforcing relationship under near stall conditions. The findings provide critical insights for analyzing flow-induced vibration failures in multistage axial compressor blades.
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