摘要
铝合金疲劳裂纹易沿粗大的杂质相粒子萌生,而合金的晶粒结构、晶界和晶粒取向、析出相等本征微观特征影响疲劳裂纹的扩展行为。从疲劳裂纹的萌生和扩展两方面较系统地分析了航空铝合金耐疲劳损伤性能与本征微结构之间的关系和作用机制以及最新的研究进展,并在此基础上提出了需要进一步研究的问题。
In terms of the fatigue crack initiation and propagation, the relationship and micro-mechanism between the microstructure properties and the fatigue performance in aluminum alloy for aeronautical applications are systematially discussed. Some possible and prospective aspects of future research orientations are also proposed. The analysis shows that the fatigue crack is prone to initiate at second phase particles, while the fatigue crack propagation performance is known to depend on a combination of several microstructure parameters： grain size and state of recrystallization, grain boundary strength and orientation, strengthening precipitates.
出处
《材料导报》
EI
CAS
CSCD
北大核心
2010年第17期134-138,共5页
Materials Reports
基金
国家重点基础研究发展规划项目(2005CB623705)
关键词
航空铝合金
微观结构
疲劳裂纹萌生与扩展
aluminum alloy, microstructure, fatigue initiation and propagation
