航空涡轮盘多轴蠕变-疲劳寿命预测及对比研究  

Multi-Axial Creep-Fatigue Life Prediction and Comparative Study of Aviation Turbine Disc

作　　者：田若洲 郭素娟[1] 游旭 TIAN Ruozhou;GUO Sujuan;YOU Xu(School of Mechanical and Power Engineering,East China University of Science and Technology,Shanghai 200237,China)

机构地区：[1]华东理工大学机械与动力工程学院,上海200237

出　　处：《力学季刊》2022年第2期249-259,共11页Chinese Quarterly of Mechanics

基　　金：国家自然科学基金(11872181)。

摘　　要：针对几种经典和新发展的蠕变-疲劳寿命模型开展综述介绍,并建立预测航空涡轮盘在循环热-机蠕变-疲劳载荷谱下蠕变-疲劳行为的数值流程,对某型航空涡轮盘的蠕变-疲劳损伤和寿命进行预测和对比.结果表明:等效应变法与临界平面法得出的疲劳损伤差距较小,等效应变法由于数值计算简单,工程适用性更强.寿命-时间分数(TF)法由于无法考虑应力松弛效应,给出了最为保守的蠕变损伤预测,其对盘体应力三轴度引起的损伤不敏感;延性耗竭法(DE)法仅以蠕变应变率作为损伤因素,虽考虑多轴蠕变因子的影响,但是给出的蠕变损伤过小;修正应变能密度耗竭(MSEDE)法综合考虑蠕变应变与应力松弛,并且考虑多轴蠕变因子与弹性跟随效应的影响,结合疲劳损伤模型可以给出合理的蠕变、疲劳损伤比例,其预测结果更加合理.A review of several classical and newly developed creep-fatigue life models is presented,and a numerical procedure for predicting the creep-fatigue behavior of an aeronautical turbine disk under cyclic thermal-mechanical creep-fatigue load spectrum is established to predict and compare the creep-fatigue damage and life of an aeronautical turbine disk.The results show that there is no big difference between the fatigue damage obtained by the equivalent strain method and the critical plane method,and the equivalent strain method is more applicable to engineering due to its simpleness in numerical calculation.the Time Fraction(TF)appraoch gives the most conservative creep damage prediction because it cannot incorporate the stress relaxation effect,and it is insensitive to the damage caused by the triaxial degree of disc stress.The Ductility Exhaustion(DE) appraoch only takes the creep strain rate as the damage cause.Although it considers the effect of multi-axial creep factor,it under-estimates the creep damage.The Modified Strain Energy Density Exhaustion(MSEDE) appraoch integrates creep strain and stress relaxation,and considers the influence of multi-axial creep factor and the elastic following effect,and can give a reasonable creep and fatigue damage ratio in combination with the fatigue damage model,with more reasonable prediction results.

关 键 词：航空涡轮盘 蠕变疲劳 寿命预测 设计标准 对比 

分 类 号：V232.3[航空宇航科学与技术—航空宇航推进理论与工程]