畸变来流下高转速叶片气弹失稳机理研究  

Research on the mechanism of aeroelastic instability of high speed blades under distorted incoming flow

作　　者：韦雪阳 陈富强 李芙东 蔡勤榕 王维民 WEI Xueyang;CHEN Fuqiang;LI Fudong;CAI Qinrong;WANG Weimin(Beijing Key Laboratory of Health Monitoring Control and Fault Self-recovery for High-end Machinery,Beijing University of Chemical Technology,Beijing 100029,China;State Key Laboratory of High-end Compressor and System Technology,Hefei 230031,China;State Key Laboratory of High-end Compressor and System Technology,Beijing University of Chemical Technology,Beijing 100029,China;Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,Department of Energy and Power Engineering,Tsinghua University,Beijing 100084,China)

机构地区：[1]北京化工大学高端机械装备健康监控与自愈化北京市重点实验室,北京100029 [2]高端压缩机及系统技术全国重点实验室,合肥230031 [3]北京化工大学高端压缩机及系统技术全国重点实验室,北京100029 [4]清华大学热科学与动力工程教育部重点实验室,北京100084

出　　处：《流体机械》2024年第11期79-86,96,共9页Fluid Machinery

基　　金：高端压缩机及系统技术全国重点实验室开放基金项目(SKL-YSJ202302);中央高校基本科研业务费专项(JD2420,buctrc202339)。

摘　　要：为了探究先进压气机侧向进气诱发的进气畸变沿高速动叶(R1)的传递规律及耦合机制,基于弱流固耦合方法和畸变来流数据对动叶气弹稳定性进行了仿真研究。结果表明:压气机畸变来流含总压畸变和旋流畸变,复合畸变诱导R1叶尖处形成沿周向传播的分离涡,而叶尖分离涡导致全周叶片在同一时刻承受不同大小和频率的气动力。经对比,气动阻尼稳定后,得到均匀进气下的气动阻尼为0.14,而畸变来流下的气动阻尼为0.1,降幅达28.57%,进气畸变显著降低动叶气弹稳定性。此外,由叶尖分离涡造成的众多集中在3倍转频附近的气流激励频率,激发了叶片低模态共振。发生共振的叶片在叶尖分离涡消失后,振动幅值仍相较于均匀进气增大2.3倍。研究结果可为先进压气机抗畸变设计及提升动叶气弹稳定性提供重要参考。In order to investigate the transmission law and coupling mechanism of intake distortion induced by lateral intake of advanced compressors along high-speed moving blades(R1),a simulation study was conducted on the aeroelastic stability of moving blades based on weak fluid-structure coupling method and distorted inflow data.The results show that the distortion of the compressor inflow includes total pressure distortion and swirl distortion.The composite distortion induces the formation of separation vortices propagating along the circumference at the R1 blade tip,and the blade tip separation vortices cause the entire blade to withstand aerodynamic forces of different sizes and frequencies at the same time.Through comparison,after stabilizing the aerodynamic damping,it is found that the aerodynamic damping under uniform intake is 0.14,while the aerodynamic damping under distorted inflow is 0.1,with a decrease of 28.57%.The intake distortion significantly reduces the aerodynamic stability of the moving blade.In addition,the numerous airflow excitation frequencies concentrating near three times the rotational frequency caused by the separation vortices at the blade tip excite low mode resonance of the blade.After the separation vortex at the blade tip disappears,the vibration amplitude of the resonant blade still increases by 2.3 times compared to uniform intake.The research results can provide important references for the anti-distortion design of advanced compressors and the improvement of aerodynamic stability of moving blades.

关 键 词：先进压气机 进气畸变 流固耦合 气弹稳定性 

分 类 号：TH45[机械工程—机械制造及自动化]