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

作　　者：董成利 范姜波 陆麒羽 石多奇[4] 郭广平 DONG Chengli;FAN Jiangbo;LU Qiyu;SHI Duoqi;GUO Guangping(AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;AECC Key Laboratory of Material Testing and Evaluation,Beijing 100095,China;Beijing Key Laboratory of Aeronautical Material Testing and Evaluation,Beijing 100095,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]中国航发北京航空材料研究院,北京100095 [2]中国航发材料检测与评价重点实验室,北京100095 [3]北京市航空材料检测与评价重点实验室,北京100095 [4]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空材料学报》2025年第2期102-109,共8页Journal of Aeronautical Materials

基　　金：国家科技重大专项(J2019-Ⅵ-0008);稳定支持项目(2019-363)。

摘　　要：针对FGH96合金带孔平板在600℃下开展疲劳实验研究,采用黏塑性本构模型计算FGH96合金带孔平板的应力和非弹性应变分布情况,结合扫描电子显微镜(SEM)对疲劳断口的微观形貌观察分析疲劳失效机理。基于SEM观测结果和FGH96合金带孔平板的几何特征,定义临界疲劳损伤参数和应力集中因子,并对连续损伤力学(CDM)模型进行修正。研究结果表明,相较于传统的疲劳寿命预测方法,考虑临界疲劳损伤和应力集中因子的改进CDM模型对FGH96合金带孔平板的疲劳寿命具有更高的预测精度,预测结果均位于实验结果的±2倍分散带以内。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 

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]