滕鹏,李振,张金刚,刘新灵

• 1:中国航发北京航空材料研究院
• 2:航空材料检测与评价北京市重点实验室
• 3:中国航空发动机集团材料检测与评价重点实验室

摘要(Abstract)：

研究了DD5、DD6单晶高温合金在应力比R=-1的高周疲劳实验中裂纹扩展特性及定量分析方法。通过观察断口宏微观结构，揭示两种材料的高周疲劳裂纹均起源于内部疏松，且在裂纹扩展第二阶段存在明显疲劳条带特征。利用Forman模型和塑性区模型定量分析裂纹扩展第二阶段应力状态。测量疲劳条带间距并结合Forman模型，计算出裂纹尖端应力强度因子幅值ΔK,结果表明反推应力与名义应力的之间误差均在1.3倍内。通过电子背散射衍射(EBSD)技术表征塑性区尺寸，结合Tresca准则反推疲劳应力，结果表明在裂纹扩展第二阶段随裂纹长度增加，塑性区尺寸相应增大，反推应力随之减小，与利用Forman模型反推结果变化规律一致，但计算误差在2～3倍内，误差大于前者。最后，本文指出未来研究方向，将考虑裂纹张开应力的影响，优化塑性区模型以更精确地表达裂纹扩展第二阶段应力状态。

关键词(KeyWords)： 镍基单晶高温合金;Forman模型;塑性区尺寸;断口定量分析

Abstract:

Keywords:

基金项目(Foundation): 国家科技重大专项(J2019-VI-0022-0138)

作者(Author): 滕鹏,李振,张金刚,刘新灵

DOI: 10.13289/j.issn.1009-6264.2025-0218

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