焊接缺陷对异种铝合金TIG对接接头疲劳行为的影响

王池权; 石亮; 张祥春; 刘志毅; 邵成伟

doi:10.13700/j.bh.1001-5965.2020.0370

焊接缺陷对异种铝合金TIG对接接头疲劳行为的影响

doi: 10.13700/j.bh.1001-5965.2020.0370

中国航空综合技术研究所, 北京 100028

基金项目:

国家重点研发计划 2018YFB1106300

详细信息

通讯作者:
王池权, E-mail: wangchiquan301@163.com

中图分类号: V261.3;TG40
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- 文章访问数: 554
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- 被引次数: 0
出版历程
- 收稿日期: 2020-07-29
- 录用日期: 2020-10-23
- 网络出版日期: 2021-07-20

Influence of welding defects on fatigue behavior of dissimilar aluminum alloy TIG butt joint

China Aero Polytechnology Establishment, Beijing 100028, China

Funds:

National Key R & D Program of China 2018YFB1106300

More Information

Corresponding author: WANG Chiquan, E-mail: wangchiquan301@163.com

摘要

摘要:
以5A06-O/7A05-T6异种铝合金钨极氩弧焊（TIG）对接接头为对象，通过疲劳试验数据和断口形貌分析，研究了气孔缺陷和未熔合缺陷对焊接接头疲劳性能的影响规律及机理。结果表明：气孔缺陷和未熔合缺陷对5A06-O/7A05-T6对接接头的疲劳性能均产生不利影响，且缺陷的大小、位置与载荷的交互作用是影响疲劳裂纹提前萌生的主要因素，同一应力水平下，疲劳裂纹更易萌生于尺寸较大且位置更接近于材料表面的焊接缺陷处，而随着应力水平的降低，焊接缺陷对焊接接头疲劳性能的不利影响更为显著；与气孔缺陷相比，未熔合缺陷边缘的应力集中效应更明显，更易导致疲劳裂纹萌生，且焊接接头组织相较于焊接母材组织更脆，疲劳裂纹以穿晶和沿晶形式交替扩展，使疲劳寿命进一步缩短。
- 铝合金 /
- 钨极氩弧焊(TIG) /
- 焊接缺陷 /
- 疲劳 /
- SEM
Abstract:
Fatigue tests and fracture morphology analyses were performed to determine the influence law and mechanism of pore defect and incomplete fusion defect on the fatigue performance of 5A06-O/7A05-T6 dissimilar aluminum alloy TIG butt joint. The results show that both pore defect and incomplete fusion defect have adverse effects on the fatigue properties of 5A06-O/7A05-T6 butt joint, and the interaction between the size and location of defects and the load is the main factor affecting the early initiation of fatigue cracks. Fatigue cracks are more likely to initiate at the welding defects with larger size and closer to the material surface under the same stress level, and the interaction between welding defects and fatigue loading increases with the decrease of stress level, and ultimately decreases the fatigue strength. Compared with pore defect, the effect of stress concentration at the edge of incomplete fusion defect is more significant, which is more likely to cause fatigue crack initiation, the microstructure of welded joint is more brittle than that of welding base metal, and the fatigue crack propagates alternately in the transgranular and intergranular form, which further shortens the fatigue life.
- aluminum alloy /
- TIG /
- welding defects /
- fatigue /
- SEM

HTML全文

图 1 5A06-O/7A05-T6对接接头疲劳测试试样

Figure 1. Fatigue test specimen of 5A06-O/7A05-T6 butt joint

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图 2 疲劳测试

Figure 2. Fatigue test

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图 3 疲劳测试结果

Figure 3. Fatigue test results

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图 4 疲劳裂纹萌生处气孔缺陷尺寸及位置测量

Figure 4. Measurement of size and location of pore defects at the position of fatigue crack initiation

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图 5 疲劳裂纹萌生处气孔缺陷尺寸及位置分布

Figure 5. Size and location distribution of pore defects at the position of fatigue crack initiation

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图 6 气孔缺陷影响系数曲线

Figure 6. Influence coefficient curve of pore defect

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图 7 未熔合缺陷图像处理过程

Figure 7. Image processing procedure of incomplete fusion defect

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图 8 未熔合缺陷比例值分布

Figure 8. Proportion distribution of incomplete fusion defects

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图 9 未熔合缺陷影响系数曲线

Figure 9. Influence coefficient curves of incomplete fusion defect

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图 10 铝合金5A06-O疲劳断口

Figure 10. Fatigue fracture of 5A06-O aluminum alloy

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图 11 5A06-O/7A05-T6对接接头疲劳断口(气孔缺陷)

Figure 11. Fatigue fracture of 5A06-O/7A05-T6 butt joint (pore defect)

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图 12 5A06-O/7A05-T6对接接头疲劳断口(未熔合缺陷)

Figure 12. Fatigue fracture of 5A06-O/7A05-T6 butt joint (incomplete fusion defect)

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表 1 5A06-O/7A05-T6焊接母材及焊丝的力学性能

Table 1. Mechanical properties of 5A06-O/7A05-T6 welding base metal and welding wire

材料	σ_b/MPa	σ_s/MPa	δ/%
5A06-O	356.4	161.8	21.14
7A05-T6	414.4	311.6	13.56
5A06-O/7A05-T6	281.08	157.33	11.43
注: σ_b为强度极限，σ_s为屈服极限，δ为延伸率。

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表 2 5A06-O/7A05-T6焊接母材及焊丝的化学成分

Table 2. Chemical composition of 5A06-O/7A05-T6 welding base metal and welding wire

材料	元素含量
5A06-O	Mg	Mn	Zn	Fe	Si	Cu	Ti	Al
5A06-O	6.2	0.62	0.23	0.13	0.12	0.11	0.03	Bal.
7A05-T6	Zn	Mg	Mn	Cu	Fe	Si	Ti	Al
7A05-T6	4.58	1.37	0.22	0.16	0.15	0.08	0.04	Bal.
ER5356	Mg	Fe	Mn	Ti	Si	Zn	Cu	Al
ER5356	4.59	0.13	0.12	0.1	0.04	0.01	0.001	Bal.
注: Bal.表示Al元素的含量为除了表中已经列出的元素含量外剩下的化学元素含量。

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表 3 试验环境

Table 3. Test environments

环境	温度/℃	试样	加载方式
干燥大气	25±3	5A06-O/7A05-T6 对接接头(气孔缺陷)	T-T恒幅加载
干燥大气	25±3	5A06-O/7A05-T6 对接接头(未熔合缺陷)	T-T恒幅加载

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表 4 疲劳S-N曲线

Table 4. Fatigue S-N curves

试样	试验环境	S-N曲线
5A06-O	干燥大气	S_max^6.02N=1.86×10¹⁹
7A05-T6	干燥大气	(S_max-240.3)^1.56N=7.8×10⁷
5A06-O/7A05-T6 焊接接头(气孔缺陷)	干燥大气	S_max^3.50N=1.08×10¹³

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表 5 未熔合缺陷影响系数拟合曲线

Table 5. Fitting curves of influence coefficient of incomplete fusion defect

S_max/MPa	未熔合缺陷影响系数曲线	相关系数R²
120	y=0.047x+1.75	0.979
90	y=0.049x+1.84	0.997
60	y=0.056x+2.21	0.983

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