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2222材料工程  2022, Vol. 50 Issue (6): 149-156    DOI: 10.11868/j.issn.1001-4381.2021.000466
  研究论文 本期目录 | 过刊浏览 | 高级检索 |
航空铝合金原位腐蚀疲劳性能及断裂机理
王付胜1, 孔繁淇1, 王文平2, 陈亚军1,*()
1 中国民航大学 中欧航空工程师学院,天津 300300
2 北京经纬恒润科技股份有限公司,北京 100191
In-situ corrosion fatigue performance and fracture mechanism of aviation aluminum alloy
Fusheng WANG1, Fanqi KONG1, Wenping WANG2, Yajun CHEN1,*()
1 China Sino-European Institute of Aviation Engineering, Civil Aviation University, Tianjin 300300, China
2 Beijing Jingwei Hirain Technologies Co., Inc., Beijing 100191, China
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摘要 

为了研究不同腐蚀条件下2024铝合金的疲劳性能,首先设计搭建原位腐蚀疲劳平台,然后分别进行无腐蚀疲劳、预腐蚀疲劳和原位腐蚀疲劳实验,分析不同腐蚀疲劳条件下2024铝合金的疲劳断裂行为,最后利用扫描电镜(SEM)表征宏、微观断口特征,探究失效机理。结果表明:相同腐蚀环境和时间下,预腐蚀和原位腐蚀疲劳寿命分别为无腐蚀疲劳寿命的92%和42%;在原位腐蚀疲劳条件下,滑移带挤入、挤出导致表面粗糙度增加,吸附较多腐蚀介质,加剧蚀坑演化,易于裂纹萌生并形成多个裂纹源。裂纹的连通形成更大尺寸的损伤,并在材料内部快速扩展。预腐蚀和原位腐蚀疲劳试件断口观察到大量脆性疲劳条带,并且原位腐蚀疲劳条带平均间距约为无腐蚀疲劳条带间距的2倍,说明原位腐蚀疲劳条件下裂纹扩展速率更快。

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关键词 航空铝合金原位腐蚀疲劳疲劳寿命断裂机理    
Abstract

In order to study the fatigue properties of 2024 aluminum alloy under different corrosion fatigue conditions, First, an in-situ corrosion fatigue platform was established, and then non-corrosion fatigue test, pre-corrosion fatigue test and in-situ corrosion fatigue test were used to comparatively study the fatigue life and fracture mechanism of 2024 aluminum alloy. Scanning electron microscopy(SEM) was used to characterize the macro and micro fracture characteristics and explore the failure mechanism. The results show that the samples with the same corrosion environment and corrosion time, the fatigue life in in-situ corrosion fatigue test and in pre-corrosion fatigue test is 92% and 42% of corrosion fatigue life, respectively. Under the condition of in-situ corrosion fatigue, the squeeze and the extrusion of slip zone leads to the increase of surface roughness, which adsorbs more corrosive medium, exacerbates pit evolution, accelerates the initiation of crack and forms multiple crack sources. The connection of cracks forms a larger size of damage, and rapidly expands inside the material. A lot of brittle fringes are observed in the fracture of the pre-corrosion and in-situ corrosion fatigue test specimens, and the average distance between the fringes under in-situ corrosion fatigue is about two times larger than that under non-corrosion fatigue, indicating the crack propagation rate is faster under the in-situ corrosion fatigue condition.

Key wordsaviation aluminum alloy    in-situ corrosion fatigue    fatigue life    fracture mechanism
收稿日期: 2021-05-15      出版日期: 2022-06-20
中图分类号:  V250.2  
  V250.3  
基金资助:中央高校基本科研业务费(3122018Z003)
通讯作者: 陈亚军     E-mail: yjchen@cauc.edu.cn
作者简介: 陈亚军(1976—),男,教授,博士,研究方向为飞机结构与材料损伤评价,联系地址: 天津市东丽区中国民航大学(北院)中欧航空工程师学院(300300),E-mail: yjchen@cauc.edu.cn
引用本文:   
王付胜, 孔繁淇, 王文平, 陈亚军. 航空铝合金原位腐蚀疲劳性能及断裂机理[J]. 材料工程, 2022, 50(6): 149-156.
Fusheng WANG, Fanqi KONG, Wenping WANG, Yajun CHEN. In-situ corrosion fatigue performance and fracture mechanism of aviation aluminum alloy. Journal of Materials Engineering, 2022, 50(6): 149-156.
链接本文:  
http://jme.biam.ac.cn/CN/10.11868/j.issn.1001-4381.2021.000466      或      http://jme.biam.ac.cn/CN/Y2022/V50/I6/149
Fig.1  试件尺寸示意图(mm)
Fig.2  原位腐蚀疲劳实验平台示意图
ConditionFatigue life/cycle
Specimen 1 Specimen 2 Specimen 3 Average
Non-corrosion 206861 197530 140198 181530
Pre-corrosion 101095 169585 233120 167933
In-situ corrosion 53598 95408 79684 76230
Table 1  不同腐蚀疲劳条件下的疲劳寿命
Fig.3  不同腐蚀疲劳条件下疲劳寿命分布
Fig.4  疲劳断口扫描电镜照片
(a)无腐蚀;(b)预腐蚀;(c)原位腐蚀
Fig.5  无腐蚀疲劳源微观形貌(1)及EDS分析(2)
(a)基体;(b)粒子
Fig.6  预腐蚀疲劳源处疏松腐蚀产物
Fig.7  原位腐蚀疲劳断口SEM图
(a)疲劳源间撕裂脊; (b)疲劳源处点蚀
Fig.8  预腐蚀疲劳试样表面点蚀坑形貌
(a)远离断口腐蚀产物; (b)断口附近腐蚀产物表面裂纹
Fig.9  原位腐蚀疲劳试件表面裂纹形貌
  无腐蚀(a)、预腐蚀(b)和原位腐蚀(c)疲劳解理形貌
Fig.11  无腐蚀(a)、预腐蚀(b)和原位腐蚀(c)疲劳条带形貌
Fig.12  疲劳条带间距测量
(a)无腐蚀;(b)预腐蚀;(c)原位腐蚀
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