拉剪复合载荷下焊接接头疲劳寿命预测方法

刘小刚; 魏昊; 章胜; 汪全中; 余嘉伟; 艾兴

doi:10.13224/j.cnki.jasp.20230441

拉剪复合载荷下焊接接头疲劳寿命预测方法

doi: 10.13224/j.cnki.jasp.20230441

1.
南京航空航天大学能源与动力学院，南京 210016
2.
中国航发湖南动力机械研究所，湖南株洲 412002

基金项目: 国家科技重大专项（J2019-Ⅳ-0008-0076）

详细信息

作者简介:
刘小刚（1977-），男，副教授，博士，主要从事结构疲劳与断裂力学方面的研究。E-mail：liuxg03@nuaa.edu.cn

中图分类号: V231.95
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出版历程
- 收稿日期: 2023-07-07
- 网络出版日期: 2024-05-20

Fatigue life prediction method of tensile and shear load of welded joints

1.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Hunan Aviation Powerplant Research Institute，Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
为了建立焊接接头拉剪多轴应力状态下的寿命预测方法，文中设计了GH4169电子束焊接头蝶形拉剪疲劳试验件，开展了不同加载角度（0°、15°、30°及45°）下的疲劳试验，获得其4种加载角度下的F-N曲线；探讨了不同剪/拉应力比γ对焊接接头疲劳性能的影响规律。采用临界距离法，确定蝶形件焊缝缺口根部的临界距离，获得焊缝平面上的有效应力参量；进而引入与γ相关的修正系数k（γ）对Findley模型中的材料参数进行修正，建立了适用于不同加载角度的统一的多轴疲劳寿命预测模型。通过与试验结果对比，验证了所提出的模型具有较高的预测精度，误差在±2倍分散带以内。
- 焊接接头 /
- 拉剪多轴疲劳 /
- Findley模型 /
- 临界距离法 /
- 疲劳寿命预测
Abstract:
In order to establish a life prediction method for welded joints under multiaxial tensile and shear stress conditions, a butterfly shaped test piece of GH4169 electron beam welded joints was designed and fatigue tests were conducted at different loading angles (0°, 15 °, 30°, and 45°) to obtain F-N curves respectively. The influences of different shear/tensile stress ratios γ on the fatigue performance of welded joints were explored. The critical distance method was applied to determine the characteristic size of the notch root of the welded pieces, and the effective stress parameters on the weld plane were obtained. Furthermore, relevant correction coefficients $ k(\gamma ) $ were introduced to modify the material parameters in the Findley model, and a unified multiaxial fatigue life prediction model suitable for different loading angles was established. By comparing with test results, it was verified that the proposed model had high prediction accuracy, with an error within ±2 times dispersion band.
- welded joint /
- multiaxial fatigue of tension and shear /
- Findley model /
- critical distance method /
- fatigue life prediction

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图 1 试验件几何尺寸图（单位：mm）

Figure 1. Geometric dimension of the test piece （unit: mm）

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图 2 试验件装夹及加载示意图

Figure 2. Schematic diagram of clamping and loading of test piece

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图 3 焊缝受力分析

Figure 3. Stress analysis of weld seam

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图 4 不同加载角度蝶形件试验装夹图

Figure 4. Test clamping diagram of butterfly test pieces with different loading angles

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图 5 不同加载角度试验件的F-N曲线

Figure 5. F-N curves of test pieces at different loading angles

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图 6 典型试验件宏观断口及裂纹萌生扩展示意图

Figure 6. Macro fracture and crack initiation and propagation of typical test pieces

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图 7 临界距离确定方法

Figure 7. Determination method of critical distance

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图 8 $ \alpha = {0{\text{°}} } $蝶形件缺口根部应力分布

Figure 8. Stress distribution at notched root of butterfly test pieces at $ \alpha = {0{\text{°}} } $

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图 9 修正Findley模型下蝶形件拉剪疲劳D-N曲线

Figure 9. D-N curve of butterfly test piece established by modified Findley model

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图 10 两种疲劳寿命预测模型预测结果对比

Figure 10. Comparison of prediction results between two fatigue life prediction models

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表 1 试验加载方案

Table 1. Test loading scheme

$ \alpha $/（°）	$\gamma $	F_max,1/kN	F_max,2/kN	F_max,3/kN	F_max,4/kN	F_max,5/kN
0	0	9.4	8.8	8.4	7.9	7.5
15	0.27	9.1	8.2	7.5	6.7	6.0
30	0.58	9.1	8.3	7.5	6.7	5.8
45	1	9.1	8.1	7.1	6.1	5.1

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表 2 α=0°蝶形件临界距离

Table 2. Critical distance of butterfly test pieces at α=0°

F/kN	$ N_{\text{f}}^{\text{*}} $/cycles	$ L{}_{\text{m}} $/mm
9.4	51733	0.48
8.8	84021	0.52
8.4	118289	0.58
7.9	185745	0.60
7.5	272172	0.64

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表 3 修正Findley模型的损伤参量

Table 3. Damage parameters based on Findley modified model

$ \alpha $/（°）	$ {F_{\max }} $/kN	$ {\sigma _{{\text{eff,n}}}} $/MPa	$ {\tau _{{\text{eff,n}}}} $/MPa	$ D $/MPa
0	9.4	908	0	817
	8.8	845	0	761
	8.4	804	0	724
	7.9	759	0	683
	7.5	721	0	649
15	9.1	859	98	894
	8.2	774	88	805
	7.5	709	80	737
	6.7	631	72	657
	6.0	569	64	591
30	9.1	797	191	955
	8.3	729	173	871
	7.5	658	156	786
	6.7	588	139	702
	5.8	509	121	609
45	9.1	761	270	1031
	8.1	680	240	920
	7.1	594	210	804
	6.1	510	180	690
	5.1	428	150	578

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