基于飞行载荷的LC9铝合金腐蚀疲劳裂纹扩展  

Fatigue Crack Growth in Corrosion Damage of LC9 Aluminum Alloy Based on Aircraft Loading

作　　者：李旭东[1] 刘治国[1] 穆志韬[1] 朱武峰[1] 

机构地区：[1]海军航空工程学院青岛校区,青岛266041

出　　处：《腐蚀与防护》2013年第11期985-988,共4页Corrosion & Protection

基　　金：国家自然科学基金(11072124)

摘　　要：通过在EXCO溶液中浸润不同时间获得了LC9铝合金不同程度的腐蚀损伤,研究了在飞行谱作用下的LC9铝合金腐蚀坑萌生裂纹的扩展行为。结果表明,腐蚀损伤会严重降低试件的疲劳寿命,且腐蚀坑深度是描述腐蚀损伤和预测疲劳寿命的合适特征参数。基于AFGROW软件对预腐蚀试件疲劳寿命进行了预测,获得了较为有价值的结果。The fatigue crack growth behavior of LC9 aluminum alloy subjected to a transport aircraft loading spectrum was studied by immersing LC9 aluminum alloy in EXCO solution for different times to produce different degrees of corrosion damage. The results show that the corrosion damage can reduce the fatigue life of LC9 aluminum alloy severely. The depth of the corrosion pit was a suitable parameter for characterizing the corrosion damage and for predicting the fatigue life of LC9 aluminum alloy using commercial fatigue crack growth software.

关 键 词：疲劳 腐蚀损伤 变幅载荷 裂纹扩展 疲劳寿命预测 

分 类 号：TG115[金属学及工艺—物理冶金]