摘要
航空发动机压气机叶片在振动台上进行疲劳试验时,振动台的简谐激励信号在经过多个工装的摩擦界面传输过程中会出现高阶倍频谐波分量。当叶片固有频率与激振频率的高阶谐波分量的频率相近时,叶片在外部简谐激励下会发生多模态耦合振动的现象,利用该试验特征可模拟航空发动机压气机叶片工作时的多模态耦合振动。通过振动疲劳多模态标定试验和激振试验,获取了叶片耦合振动时位移和应变的振动特性。数值分析和试验结果表明:叶片发生失效的位置与耦合振动各阶模态叠加后的振动大应力位置一致;随着叶片固有频率与高阶谐波分量频率之间频差的增加,高阶模态的振动应力呈指数下降的趋势。
During fatigue tests of aviation engine compressor blades on a shaking table,high-order harmonic components appear in transmitting process of simple harmonic excitation signal of shaking table passing through friction interfaces of multi-tooling.When natural frequencies of blade are close to frequencies of higher-order harmonic components of excitation frequency,blade can have multimodal coupled vibration under external simple harmonic excitation.This test feature can be used to simulate multimodal coupled vibration of compressor blades of aviation engine during operation.Here,vibration characteristics of blade’s displacement and strain during its coupled vibration were obtained with vibration fatigue multimodal calibration tests and excitation tests.Numerical analysis and test results showed that positions of blade failures are consistent to positions of large vibration stresses after superposition of various modes in coupled vibration;with increase in frequency differences between blade natural frequencies and higher-order harmonic frequencies,vibration stresses of higher-order modes decrease exponentially.
作者
李鑫
陈官峰
秦秀云
程前
潘容
王春健
张呈波
LI Xin;CHEN Guanfeng;QIN Xiuyun;CHENG Qian;PAN Rong;WANG Chunjian;ZHANG Chengbo(AECC Sichuan Gas Turbine Research Institute,Chengdu 610500,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Tianjin Aerospace Reliability Technology Co.,Ltd.,Tianjin 300450,China)
出处
《振动与冲击》
EI
CSCD
北大核心
2024年第5期338-344,共7页
Journal of Vibration and Shock
关键词
压气机叶片
耦合振动
多模态共振
模态叠加
compressor blade
coupled vibration
multi-modal resonance
modes superposition
