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经过多个工装的摩擦界面传输过程中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。本文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：a）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；b）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。
Abstract
During the fatigue test of compressor blades in an aviation engine on a vibration table, the high-order harmonic components appear when the harmonic excitation signal of the shaking table is transmitted through the friction interface of several tooling. When the natural frequency of the blade is close to the frequency of the high-order harmonic component of the excitation frequency, the blade will have multi-mode coupling vibration under external harmonic excitation which can be used to simulate the multi-order coupling vibration of aero-engine compressor blades. This article obtained the vibration characteristics of displacement and strain during blade coupled vibration through vibration fatigue multi-mode calibration tests and excitation tests. Numerical analysis and experimental results show that: a) the position of blade failure is consistent with the position of high stress after the superposition of coupled vibration modes; b) with the increase of frequency difference between blade natural frequency and higher-order harmonic component frequency, the vibration stress of higher-order modes decreases exponentially.
关键词
压气机叶片 /
耦合振动 /
多模态共振 /
模态叠加。
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Key words
Compressor Blades /
Coupled Vibration /
Multi-mode Resonance /
Mode Superposition.
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