航空材料学报2025，Vol.45Issue(2)：102-109,8.DOI:10.11868/j.issn.1005-5053.2024.000082
FGH96合金带孔平板疲劳失效机理及寿命预测方法研究
Research on fatigue failure mechanism and life prediction method of FGH96 flat plate with a hole
摘要
Abstract
Fatigue tests were conducted on FGH96 flat plates containing a hole at 600℃.Utilizing a viscoplastic constitutive model,the stress and plastic strain distributions within these plates were meticulously calculated.Scanning electron microscopy(SEM)was employed to analyze the fatigue failure mechanism.Based on SEM observations and the geometric attributes of the FGH96 plates with holes,the critical fatigue damage and stress concentration coefficient were defined.Subsequently,the CDM(cumulative damage model)was refined accordingly.The findings revealed that,in comparison to conventional fatigue life prediction techniques,the revised CDM model,which incorporates critical fatigue damage and stress concentration coefficients,exhibited enhanced prediction accuracy for the fatigue life of FGH96 flat plates with holes.Notably,all prediction results fell within a±2 error band.关键词
带孔平板/疲劳/失效机理/寿命预测/连续损伤力学Key words
flat plate with a hole/fatigue/failure mechanism/life prediction/cumulative damage model分类
航空航天引用本文复制引用
董成利,范姜波,陆麒羽,石多奇,郭广平..FGH96合金带孔平板疲劳失效机理及寿命预测方法研究[J].航空材料学报,2025,45(2):102-109,8.基金项目
国家科技重大专项(J2019-Ⅵ-0008) （J2019-Ⅵ-0008）
稳定支持项目(2019-363) （2019-363）
