论文部分内容阅读
本文通过对航空发动机冷端盘燕尾槽子构件及其材料钛合金ＴＣ１１ 的小裂纹扩展行为和疲劳的试验研究，燕尾槽子构件小裂纹的应力强度因子权函数解的分析研究，并利用塑性诱导的Ｎｅｗ ｍ ａｎ 裂纹闭合模型，建立起从裂纹开始萌生的燕尾槽槽底疲劳全寿命预测模型。结果表明，该模型预测子构件的疲劳寿命的误差在工程所允许的二倍寿命以内
In this paper, we study the small crack growth behavior and fatigue of a dovetail trough member and its material titanium alloy TC11 on a cold aero engine, and analyze the weight function solutions of the small cracks in the dovetail trough member. The plastic-induced New m an crack closed model, establish fatigue life prediction model of dovetail groove bottom from initiation of cracks. The results show that this model predicts the error of the fatigue life of subcomponents within twice the life allowed by the project