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材料工程  2016, Vol. 44 Issue (6): 98-103    DOI: 10.11868/j.issn.1001-4381.2016.06.015
  测试与表征 本期目录 | 过刊浏览 | 高级检索 |
孔边倒角和预腐蚀作用下航空铝合金疲劳性能及断裂机理研究
周松1,2, 王磊1, 马闯1, 杨林青1, 许良1, 回丽1
1. 沈阳航空航天大学 航空制造工艺数字化国防重点学科实验室, 沈阳 110136;
2. 东北大学 机械工程与自动化学院, 沈阳 110004
Fatigue Properties and Fracture Mechanism of Aluminum Alloy with Orifice Chamfer and Pre-corrosion Damage
ZHOU Song1,2, WANG Lei1, MA Chuang1, YANG Lin-qing1, XU Liang1, HUI Li1
1. Key Laboratory of Fundamental Science for National Defense of Aeronautical Digital Manufacturing Process, Shenyang Aerospace University, Shenyang 110136, China;
2. Department of Mechanical Engineering and Automation, Northeastern University, Shenyang 110004, China
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摘要 基于航空铝合金带孔结构材料在服役过程中常因腐蚀损伤而导致疲劳断裂问题,通过对未腐蚀和预腐蚀24h后的7075铝合金双孔未倒角和双孔倒角试样进行疲劳实验研究,分析腐蚀预损伤和孔边倒角对试件疲劳性能的影响及疲劳断裂特性差异。结果表明:腐蚀预损伤对7075铝合金材料疲劳寿命的影响显著,双孔未倒角和倒角试样预腐蚀24h后试样中值疲劳寿命比未腐蚀试样最大下降了31.74%和26.92%;孔边倒角对材料疲劳寿命有一定的影响,未腐蚀和预腐蚀24h孔边倒角试样中值疲劳寿命比未倒角试样最大下降了28.02%和15.36%,主要原因是由于孔边倒角过程中产生加工刀痕,引入了"预损伤",且倒角后疲劳裂纹萌生位置变多,导致材料发生疲劳断裂的概率变大。
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周松
王磊
马闯
杨林青
许良
回丽
关键词 铝合金孔边倒角腐蚀预损伤腐蚀坑疲劳断裂    
Abstract:Fatigue fracture often occurs because of the corrosion damage to aerospace structural aluminum alloy with holes. Fatigue tests of 7075 aluminum alloy of both unchamfered and chamfered double-hole specimens under uncorrosion and 24h pre-corrosion were carried out. The influence of both pre-corrosion damage and orifice chamferer on fatigue properties and the differences of fatigue fracture characteristics were analyzed. The results show that the effect on fatigue life of pre-corrosion damage is significant. Median fatigue lives of both unchamfered and chamfered double-hole specimens under 24h pre-corrosion decrease about 31.74% and 26.92% compared with uncorrosion specimens. The orifice chamferer have a certain effect on fatigue life of both uncorrosion and 24h pre-corrosion specimens, with median fatigue lives decreased about 28.02% and 15.36% compared with unchamfered specimens, the main reason is due to the stress concentration after orifice chamfered, on the other hand, cutting marks lead to pre-damage during the orifice chamfering process which will result in an increase of the fatigue crack initiation sites and the fracture probability.
Key wordsaluminum alloy    orifice chamfer    pre-corrosion damage    corrosion pit    fatigue    fracture
收稿日期: 2015-05-15      出版日期: 2016-06-13
中图分类号:  V252  
  V216  
通讯作者: 回丽(1965-),女,教授,博士后,从事结构强度及完整性评定方面的研究,联系地址:辽宁省沈阳市沈北新区道义南大街37号 沈阳航空航天大学航空制造工艺数字化国防重点学科实验室(110136),E-mail:syhuili@126.com     E-mail: syhuili@126.com
引用本文:   
周松, 王磊, 马闯, 杨林青, 许良, 回丽. 孔边倒角和预腐蚀作用下航空铝合金疲劳性能及断裂机理研究[J]. 材料工程, 2016, 44(6): 98-103.
ZHOU Song, WANG Lei, MA Chuang, YANG Lin-qing, XU Liang, HUI Li. Fatigue Properties and Fracture Mechanism of Aluminum Alloy with Orifice Chamfer and Pre-corrosion Damage. Journal of Materials Engineering, 2016, 44(6): 98-103.
链接本文:  
http://jme.biam.ac.cn/CN/10.11868/j.issn.1001-4381.2016.06.015      或      http://jme.biam.ac.cn/CN/Y2016/V44/I6/98
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