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介绍了航空发动机联轴器TC4钛合金膜盘振动疲劳的试验研究。通过建立闭环控制下的振动疲劳试验系统,得到了该膜盘在不同激励条件下的频率-位移响应曲线,由此阐明了联轴器膜盘在大挠度条件下的非线性振动特性。基于该特性进一步开展膜盘在非线性振动条件下的振动疲劳试验研究,给出了该膜盘的径向应力-疲劳寿命曲线以及疲劳极限值。最后分析了膜盘振动疲劳的主要破坏形式。结果表明,膜盘疲劳极限值介于其母体材料的中值疲劳极限值和高可靠度疲劳极限值之间,而主要破坏形式包括可见表面裂纹和表面剥落。
The experimental research on the vibration fatigue of TC4 titanium alloy diaphragm of aeroengine coupling was introduced. By establishing a vibration fatigue test system under closed-loop control, the frequency-displacement response curves of the diaphragm under different excitation conditions are obtained, and the nonlinear vibration characteristics of the diaphragm under large deflection are clarified. Based on this characteristic, the vibration fatigue test of diaphragm under non-linear vibration was further studied. The radial stress-fatigue life curve and the fatigue limit of the diaphragm were given. Finally, the main failure modes of diaphragm vibration fatigue are analyzed. The results show that the fatigue limit of the disk is between the median fatigue limit of the parent material and the high reliability limit of fatigue, while the major failure modes include visible surface cracks and surface flaking.