镍基高温合金的热机械疲劳寿命预测模型研究  

Research on Thermo-mechanical Fatigue Life Prediction Model of Ni-base Superalloy

作　　者：崔海涛[1] 钱春华 CUI Haitao;QIAN Chunhua(College of Energy and Power Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing,210016)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《中国机械工程》2024年第1期67-73,82,共8页China Mechanical Engineering

基　　金：国家自然科学基金(91860111)。

摘　　要：针对发动机热端部件常用材料镍基高温合金GH4169进行了200~450℃及400~650℃条件下的同相位热机械疲劳(TMF)试验,考虑TMF条件下多晶材料在弹性阶段产生的微观损伤应变能,提出一种适用于多晶材料的TMF寿命预测模型,并结合试验数据确定模型参数;采用GH4169、IN718、DD8三种高温合金对该模型的TMF寿命预测能力进行评估,结果表明,提出的寿命模型预测精度高于TMF寿命预测常用的Manson-Coffin模型和Ostergren模型。In phase TMF tests on nickel-based high-temperature alloy GH4169,a commonly used material for engine hot end components,under conditions of 200450℃and 400650℃is conducted.Considering the micro damage strain energy of polycrystalline materials in the elastic stages under the condition of TMF,a TMF life prediction model suitable for polycrystalline materials was proposed,model parameters were determined by combining the TMF test data.Three superalloys,GH4169,IN718,DD8,were used to evaluate the TMF life prediction ability of this model.The prediction accuracy of the life model is higher than that of the Manson-Coffin model and Ostergen model commonly used for TMF life prediction.

关 键 词：镍基高温合金 热机械疲劳(TMF) 损伤应变能 寿命预测 

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]