Creep-fatigue lifetime prediction of GH720Li superalloy considering effect of grain size  

考虑晶粒尺寸影响的GH720Li高温合金的蠕变-疲劳寿命预测

作　　者：Bin ZHANG Rong-qiao WANG Dian-yin HU Hong-bo LI Kang-he JIANG Jia-ming WEI Hong ZHANG 张斌;王荣桥;胡殿印;李洪波;蒋康河;魏佳明;张宏(杭州市北京航空航天大学国际创新研究院,杭州311115;北京航空航天大学航空发动机研究院,北京100191;航空发动机结构强度北京市重点实验室,北京100191;中小型航空发动机联合研究中心,北京100191;清华大学航天航空学院,北京100084;中国航发湖南动力机械研究所,株洲412002;杭州汽轮动力集团股份有限公司,杭州310000;四川大学灾变力学与工程防灾四川省重点实验室,成都610065)

机构地区：[1]Hangzhou International Innovation Institute,Beihang University,Hangzhou 311115,China [2]Research Institute of Aero-engine,Beihang University,Beijing 100191,China [3]Beijing Key Laboratory of Aero-engine Structure and Strength,Beijing 100191,China [4]United Research Center of Mid-Small Aero-engine,Beijing 100191,China [5]School of Aerospace Engineering,Tsinghua University,Beijing 100084,China [6]Hunan Aviation Powerplant Research Institute,Aero Engine(Group)Corporation of China,Zhuzhou 412002,China [7]Hangzhou Turbine Power Group Co.,Ltd.,Hangzhou 310000,China [8]Failure Mechanics and Engineering Disaster Prevention,Key Laboratory of Sichuan Province,Sichuan University,Chengdu 610065,China

出　　处：《Transactions of Nonferrous Metals Society of China》2025年第3期863-871,共9页中国有色金属学报(英文版)

基　　金：financially supported by the National Natural Science Foundation of China(Nos.52306183,12272245,11832007,12172238);the Natural Science Foundation of Zhejiang Province,China(No.LQ23E050022);the Natural Science Foundation of Sichuan Province,China(Nos.2022NSFSC0324,2022JDJQ0011);the Open Project of Failure Mechanics and Engineering Disaster Prevention,Key Laboratory of Sichuan Province,China(No.FMEDP202305)。

摘　　要：In order to accurately evaluate the creep-fatigue lifetime of GH720Li superalloy,a lifetime prediction model was established,reflecting the interaction between creep damage and low-cycle fatigue damage.The creep-fatigue lifetime prediction results of GH720Li superalloy with an average grain size of 17.3μm were essentially within a scatter band of 2 times,indicating a strong agreement between the predicted lifetimes and experimental data.Then,considering that the grain size of the dual-property turbine disc decreases from the rim to the center,a grain-size-sensitive lifetime prediction model for creep-fatigue was established by introducing the ratio of grain boundary area.The improved model overcame the limitation of most traditional prediction methods,which failed to reflect the relationship between grain size and creep-fatigue lifetime.为了准确评估GH720Li高温合金的蠕变-疲劳寿命,建立了反映蠕变损伤与低循环疲劳损伤交互作用的寿命预测模型。平均晶粒尺寸为17.3μm的GH720Li高温合金的蠕变-疲劳寿命预测结果基本在2倍分散带内,表明预测寿命与试验结果吻合良好。考虑到双性能涡轮盘的晶粒尺寸从边缘向中心逐渐减小,通过引入晶界面积比,建立了晶粒尺寸敏感的蠕变-疲劳寿命预测模型,克服了大多数传统预测方法难以反映晶粒尺寸与蠕变-疲劳寿命关系的缺点。

关 键 词：CREEP-FATIGUE lifetime prediction GH720Li superalloy grain size damage accumulation 

分 类 号：TG1[金属学及工艺—金属学]