基于小裂纹断裂力学的冷端盘燕尾槽疲劳全寿命预测技术研究

FATIGUE LIFE PREDICTION OF TENONS IN AEROENGINE COLD-SECTION DISCS BASED ON SMALL CRACK GROWTH

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。

Tests for small and large crack growth were conducted on substructure model of tenon in the aeroengine cold section disc which was made of Titanium alloy TC11.Stress intensity factor solution of the substructure was obtained by FEM and its weight functions were analyzed.Plasticity introduced Newman Crack Closure model was used to predict the total fatigue life of the substructure,in which small crack was initiated from swallow-tailed groove bottom.Prediction results are in good agreement with tested results.