镍基高温合金疲劳-蠕变寿命预测的临界面损伤方法

采用临界面损伤方法并耦合疲劳-蠕变寿命模型,通过适当的技术改进,分别对某型航空发动机650℃条件下涡轮盘用材料ZSGH4169高温合金和980℃条件下涡轮转子叶片用材料DZ125定向凝固高温合金的疲劳-蠕变寿命进行预测,并分别比较以W_(alls),C_(cb),S_(wt),G_(lk),和Fin为参数的五种寿命模型的预测精度。算例的计算结果表明:对于ZSGH4169高温合金,以Walls临界损伤平面为参数的寿命模型预测效果较好,预测的结果与实验值相比基本落在±3倍分散带以内;而对于DZ125高温合金而言,以G_(lk)临界损伤平面为参数的寿命模型预测效果较好,预测的结果与实验值相比基本落在±2.5倍分散带以内。

Critical Plane Damage Method for Fatigue-creep LifePrediction of Nickel-based Superalloy

Adopting the classical critical plane damage method coupling fatigue-creep life models with adequate technique modification, the life predications of ZSGH4169 superalloy at 650 ℃and DZ125 superalloy at 980 ℃ were investigated to compare the predication accuracies of the five kinds of fatigue-creep life models, i.e.based on Walls, Ccb, Swt, Glk and Fin.The results of typical examples show that the fatigue-creep model based on Walls is the best for ZSGH4169 superalloy at 650 ℃,and the predicted life falls within ±3 scatter band of the test data, while the fatigue-creep model based on Glk is the best for DZ125 superalloy at 980 ℃, and the predicted life falls within ±2.5 scatter band of the test data.