高低周载荷作用下燕尾榫结构的微动疲劳寿命预测  

Prediction of fretting fatigue life of dovetail joint under high-cycle and low-cycle load

作　　者：古远兴[1] 温卫东[1] 崔海涛[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2008年第2期240-243,共4页Journal of Propulsion Technology

摘　　要：为预测在高周和低周载荷共同作用下,燕尾榫连接结构的微动疲劳寿命,采用高低周等效应力比代替传统经验预测模型中的等效应力,并考虑到摩擦功的影响,对微动疲劳寿命预测经验模型进行改进。通过燕尾榫连接结构的高低周微动疲劳试验,拟合了改进微动疲劳寿命预测模型中的三个系数;采用该模型对相关文献中的燕尾榫连接结构微动疲劳试验结果进行预测,结果表明,微动疲劳寿命预测的最大误差降低了约50%。For the fretting fatigue life prediction of component under high cycle load and low cycle load, the equivalence stress ratio of high cycle load and low cycle load was substituted for the equivalence stress. An improved experiential model was obtained. The parameters of the improved model were evaluated by the fretting fatigue test on dovetail joint. With the experimental results of other preferences, the improved experiential model is valid and rational. The maximum error of the prediction fretting fatigue decreases nearly 50%.

关 键 词：微动疲劳 寿命预测 载荷 燕尾榫 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]