不同应力幅比加载下2A12铝合金的多轴疲劳性能

doi:10.11868/j.issn.1001-4381.2016.000817

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摘要

采用SDN100/1000电液伺服拉扭复合疲劳试验机对2A12铝合金进行不同应力幅比下的多轴疲劳实验，观察试样断口形貌并结合加载过程中的疲劳循环曲线进行失效机理分析。结果表明：单级加载条件下，随应力幅比的增加合金的疲劳寿命提高，纯扭转条件下断面存在平整的光滑区域，随应力幅比的增加断面划痕减少，并能观察到疲劳条带以及鱼骨状、鳞片状和蜂窝状特殊形貌；不同应力幅比累积路径下，多轴疲劳寿命随一级加载周次变化的规律不同；高-低应力幅比累积路径下，拉压方向一级高应力幅比加载阶段出现明显的循环硬化现象，材料产生"锻炼效应"。

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	陈亚军
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	吴悦雷

关键词 ： 2A12铝合金, 应力幅比, 多轴疲劳, 失效机理, 锻炼效应

Abstract：

The multiaxial fatigue behavior of 2A12 aluminum alloy was studied with SDN100/1000 electro-hydraulic servo tension-torsion fatigue tester under different stress amplitude ratios, the fracture morphology and the fatigue loading curve were observed to study the failure mechanism. The results show that, under the one stage loading condition, the fatigue life prolongs with the stress amplitude ratio increasing. Under pure torsion loading, smooth and even area exists in the fracture surface. As the stress amplitude ratio increases, the number of scratch reduces, the fatigue striation and some special morphology such as the fishbone pattern, scale pattern and honeycomb pattern can be observed; under cumulative paths of different stress amplitude ratios, the variation of multiaxial fatigue life changes with first stage loading cycles; under cumulative paths of high-low stress amplitude ratio, the cycle hardening occurs obviously in the axial direction for the first stage high stress amplitude ratio loading and 2A12 alloy shows training effect.

Key words： 2A12 aluminum alloy stress amplitude ratio multiaxial fatigue failure mechanism training effect

收稿日期: 2016-07-06 出版日期: 2017-09-16

中图分类号:

O346.2

基金资助:国家自然科学基金项目(11502285);中央高校基本科研业务费中国民航大学专项资金项目(3122017112)

通讯作者: 陈亚军 E-mail: 2292598008@qq.com

作者简介: 陈亚军(1976-), 男, 博士, 副教授, 主要研究方向为飞机结构材料失效分析, 联系地址:天津市东丽区津北公路2898号中国民航大学(北院)中欧航空工程师学院(300300), E-mail:2292598008@qq.com

引用本文:

陈亚军, 王先超, 王付胜, 周剑, 吴悦雷. 不同应力幅比加载下2A12铝合金的多轴疲劳性能[J]. 材料工程, 2017, 45(9): 136-142.
Ya-jun CHEN, Xian-chao WANG, Fu-sheng WANG, Jian ZHOU, Yue-lei WU. Multiaxial Fatigue Properties of 2A12 Aluminum Alloy Under Different Stress Amplitude Ratio Loadings. Journal of Materials Engineering, 2017, 45(9): 136-142.

链接本文:

http://jme.biam.ac.cn/CN/10.11868/j.issn.1001-4381.2016.000817 或 http://jme.biam.ac.cn/CN/Y2017/V45/I9/136

Fig.1 疲劳试件尺寸图

Fig.2 2A12铝合金多轴疲劳寿命与应力幅比关系曲线

Fig.3 不同应力幅比下试样断裂外观形貌
(a)λ=0;(b)λ=0.5;(c)λ=1;(d)λ=

;(e)λ=2

Fig.4 不同应力幅比下裂纹扩展区微观形貌
(a)λ=0;(b)λ=0.5;(c)λ=1;(d)λ=

;(e)λ=2

Fig.5 应力幅比为1时瞬断区蜂窝状形貌

Table 1 应力幅比累积实验结果

Fig.6 二级损伤比与一级损伤比关系曲线
(a)2→0.5;(b)0.5→2

Fig.7 疲劳寿命与一级加载周次关系曲线

Fig.8 两类累积方式断口微观形貌
(a)2→0.5, 一级加载2000周次; (b)2→0.5, 一级加载10000周次; (c)0.5→2, 一级加载2000周次; (d)0.5→2, 一级加载10000周次

Fig.9 不同累积方式下位移及扭角幅值随时间变化曲线
1-一级循环2000周次；2-一级循环10000周次
(a)2→0.5拉压方向; (b)2→0.5扭转方向; (c)0.5→2拉压方向; (d)0.5→2扭转方向

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