铝合金构件拉伸与疲劳断裂分析  

Fracture Analysis of Aluminum Alloy Specimen under Tension and Fatigue

作　　者：张正贵[1] 曲家惠[1] 任传富[2] 黄涛[1] 王福[1] 

机构地区：[1]东北大学材料与冶金学院,沈阳110004 [2]沈阳大学材料科学系,沈阳110044

出　　处：《有色金属》2007年第1期17-20,共4页Nonferrous Metals

基　　金：辽宁省教育厅科学研究计划资助项目(20040235)

摘　　要：在应力控制下,分析带有涂层的LY12CZ铝合金构件疲劳断裂方式。结果表明,拉伸断裂和疲劳断裂位置和方式是完全不同的。疲劳是在各个铆孔处均有裂纹萌生,但其中有一处发展为主裂纹,扩展距离较长,最后与其他裂纹汇合,最终导致在铆孔位置疲劳断裂。而拉伸时是铆钉剪切断裂,铆孔完整,无破坏迹象。The fatigue fracture mode of LY12CZ aluminum alloy specimen with coating is investigated under stress control condition. The results show that the site and mode of fracture under tension and fatigue are completely different. Under fatigue condition, the cracks are initiated from every rivet holes, but one of these cracks is propagated longer and developed into the main crack, which finally is converged with other cracks and leads to the fatigue fracture on the rivet holes. However, shear fracture occurs on the rivets under tensile condition, the rivet holes are complete and no damage is observed on the rivet holes.

关 键 词：金属材料 铝合金 构件 疲劳断裂 

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] TG146.21[一般工业技术—材料科学与工程]