摘要
某ZL205A铸造铝合金飞机框架结构件在经过技术标准下的振动试验后发生断裂失效,通过宏观视察、X射线探伤、荧光渗透无损检测、断口形貌观察、微观组织分析、化学成分分析、力学性能测试等手段对该中层支架进行失效分析。结果表明,倒角部位近表面疏松的铸造缺陷是导致疲劳断裂的主要诱因。铝合金铸造疏松的几何尺寸及其呈现的空间树突状结构特点,对于疲劳裂纹的萌生和扩展有着特殊影响。
An aircraft frame component of ZL205A casting aluminum alloy fractured during former vibration-fatigue test.Failure analysis was carried out for the frame component by visual examination,X-ray detection,phosphor penetration NDT,fractography inspection,microstructure observation,chemical composition analysis and mechanical properties test.The results show that the fracture was induced maily by fatigue cracking initiations at the chamfering surface porosity defects.The geometric size of porosity defects and their intergranular spatial dendrictic shapes had special influence on the initiation and propagation of fatigue cracks was discussed.
出处
《金属热处理》
CAS
CSCD
北大核心
2011年第9期83-87,共5页
Heat Treatment of Metals
关键词
铸造铝合金
疲劳断裂
疏松缺陷
失效分析
casting aluminum alloy
fatigue fracture
porosity defect
failure analysis
