原位自生TiB<sub>2</sub>/7050铝基复合材料高周疲劳特性

段敏鸽; 李晨; 李彪; 李亚智

原位自生TiB₂/7050铝基复合材料高周疲劳特性

段敏鸽¹,
李晨²,
李彪¹,
李亚智^1, ,

1.
西北工业大学　航空学院, 西安 710072
2.
西安航天动力研究所　液体火箭发动机技术重点实验室, 西安 710100

基金项目: 国家科技重大专项 (J2019-I-0016-0015)，中国航空发动机集团产学研合作项目 (HFZL2019 CXY015)

详细信息

通讯作者:
李亚智，博士研究生，教授，博士生导师，研究方向为复合材料及其结构力学性能、结构疲劳与断裂、飞机结构耐久性/损伤容限，　E-mail: yazhi.li@nwpu.edu.cn

中图分类号: TB331
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出版历程
- 收稿日期: 2022-11-17
- 修回日期: 2022-12-16
- 录用日期: 2022-12-17
- 网络出版日期: 2023-01-18

Study on the high cycle fatigue properties of in-situ TiB₂/7050 composite

Minge DUAN¹,
Chen LI²,
Biao LI¹,
Yazhi LI^{1
, ,}

1.
School of Aeronautics, Northwestern Polytechnical University, Xi’an, 710072, China
2.
National Key Laboratory of Science and Technology on Liquid Rocket Engines, Xi’an Aerospace Propulsion Institute, Xi’an 710100, China

Funds: National Science and Technology Major Project (J2019-I-0016-0015); Aero Engine Corporation of China Industry-University-Research Cooperation Project (No. HFZL2019 CXY015)

摘要

摘要: 陶瓷颗粒增强铝基复合材料是一种将单一或多种陶瓷颗粒通过物理(外加，非原位合成)或化学(原位自生)反应合成方式融入铝合金材料中形成的多相材料，结合了陶瓷材料高硬度、耐高温、耐腐蚀等和铝合金材料良好的韧性和塑性加工特性等的性能特点，具有高比强度、高比刚度、广泛的合金基体选择范围、原材料成本低、制造和热处理工艺多样化等优势，且具有良好的抗疲劳、耐磨损、导电性和导热性，受到了工业界的广泛关注。原位自生TiB₂/Al复合材料为我国自主研发的新型铝基复合材料，是我国自主研发大飞机起落架与机身的连接结构和民用大涵道比涡扇发动机的风扇和压气机叶片机等重大装备的潜在结构材料。然而，该材料的疲劳特性研究尚不完善，疲劳试验数据还不够充分。本文以颗粒体积分数为3.67%的原位自生TiB₂/7050复合材料(in-situ TiB₂/7050)为研究对象，开展了其高周疲劳特性试验研究，并与7050铝合金(7050-Al)进行对比。试验结果表明，在相同的疲劳载荷下，in-situ TiB₂/7050的疲劳寿命明显高于7050-Al；应力比为0.1和0.5时，复合材料的疲劳极限较7050铝合金分别提高了24.59%和13.56%。以上结果说明TiB₂颗粒引入后，in-situ TiB₂/7050的疲劳裂纹萌生阻抗显著增加。开展了不同应力集中系数下的疲劳寿命对比，结果表明颗粒引入后一定程度上限制了复合材料基体的塑性变形而提高了其缺口敏感性，因此in-situ TiB₂/7050缺口敏感性高于7050铝合金；尽管如此，in-situ TiB₂/7050在存在缺口情况下的寿命仍高于7050铝合金。上述研究表明，in-situ TiB₂/7050是一种潜在的新型航空结构轻量化材料，有望代替传统铝合金，实现结构静强度和疲劳性能的共同提升。1in-situ TiB₂/7050和7050-Al疲劳寿命曲线对比: (a) R=0.1; (b) R=0.52不同应力比下疲劳寿命曲线对比: (a) in-situ TiB₂/7050; (b) 7050-Al.
- 颗粒增强铝基复合材料 /
- 高周疲劳 /
- 颗粒强化 /
- 缺口效应
Abstract: In-situ TiB₂/Al composite is a new type of aluminum matrix composite, which has the advantages of high specific strength and specific stiffness, good performances on wear resistance, electrical conductivity and thermal conductivity, a variety of matrix alloy candidates, low raw material cost, simple and diversified manufacturing and heat treatment processes. The existing research on the fatigue of in-situ TiB₂/Al composites mainly focuses on the strengthening mechanism in micro-scale and the general understanding of its fatigue performance is not sufficient. It is also lack of fatigue test data of in-situ TiB₂/Al composite for the engineering use. High cycle fatigue properties of the in-situ TiB₂ particle reinforced 7050 aluminum alloy composite (in-situ TiB₂/7050) were experimentally investigated with comparison to 7050-Al, the matrix alloy of the composite. The results reveal that the fatigue strength of the in-situ TiB₂/7050 is apparently higher than that of 7050-Al. The fatigue limits of in-situ TiB₂/7050 are improved by 24.59% and 13.56% for stress ratios 0.1 and 0.5 separately, resulting from the increase of fatigue resistance induced by the tiny TiB₂ particles. The results at different stress concentration levels show that the notch sensitivity of in-situ TiB₂/7050 is higher than that of 7050-Al, which may attribute to TiB₂ particles impeding the plastic deformation of the aluminum alloy matrix in the composite. Despite the higher notch sensitivity, the fatigue resistance the notched composite is still higher than that of the 7050-Al. Therefore, in-situ TiB₂/7050 is a promising material for lightweight structure application to replace traditional aluminum alloy in certain circumstances and achieve the joint improvement of static strength and fatigue performance.
- in-situ particle reinforced aluminum matrix composite /
- high cycle fatigue /
- particle strengthening /
- notch effect

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图 1 高周疲劳试样形状及尺寸(单位：mm)

Figure 1. Geometry of high cycle fatigue specimen (Unit: mm)

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图 2 环槽缺口试件形式和尺寸：(a) V型缺口，R0.2；(b) 圆弧缺口，R1和R3(单位：mm)

Figure 2. Geometry of notched specimens: (a) V-type notch, notch root radius R0.2; (b) Arc notch, notch radius R1 and R3 (Unit: mm)

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图 3 环槽缺口试样最小截面沿径向由中心至缺口应力分布变化

Figure 3. Tensile stress distributions of notched bar specimens from center to notch edge of the minimum section

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图 4 HCF典型断口形貌，疲劳裂纹萌生于: (a)和(b) in-situ TiB₂/7050，近表面夹杂处萌生和表面萌生; (c) 7050-Al，表面萌生

Figure 4. Fatigue fractography, cracks initiate sites: (a) and (b) in-situ TiB₂/7050, near surface and surface; (c) 7050-Al, surface.

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图 5 in-situ TiB₂/7050近表面夹杂疲劳裂纹源扫描电镜图: (a) 二次电子模式; (b) 背散模式; (c) 图(b)中箭头所示部位EDS元素分析

Figure 5. SEM photographs of a fatigue crack initiated from a near-surface inclusion in the in-situ TiB₂/7050: (a) SE mode; (b) BSE mode; (c) EDS element analysis of the site in (b) pointed by arrow

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图 6 in-situ TiB₂/7050高周疲劳断口疲劳辉纹

Figure 6. The typical fatigue striation of in-situ TiB₂/7050 in HCF fracture surface

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图 7 in-situ TiB₂/7050和7050-Al疲劳寿命曲线对比: (a) R=0.1; (b) R=0.5

Figure 7. S-N curves of in-situ TiB₂/7050 and 7050-Al: (a) R=0.1; (b) R=0.5

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图 8 不同应力比下疲劳寿命曲线对比: (a) in-situ TiB₂/7050; (b) 7050-Al

Figure 8. The S-N curves comparison of different stress ratio: (a) in-situ TiB₂/7050; (b) 7050-Al

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图 9 缺口试样NRB-R3的典型疲劳断口(裂纹从表面起始)，(a) in-situ TiB₂/7050; (b) 7050-Al

Figure 9. Typical fatigue fractography of NRB-R3 specimens (initiated from surfaces): (a) in-situ TiB₂/7050; (b) 7050-Al

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图 10 不同应力集中系数下疲劳寿命对比: (a) 7050-Al; (b) in-situ TiB₂/7050

Figure 10. The S-N curves comparison at different stress concentration: (a) 7050-Al; (b) in-situ TiB₂/7050

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表 1 in-situ TiB₂/7050和7050-Al拉伸性能

Table 1. Tensile properties of in-situ TiB₂/7050 and 7050-Al

Material	E/GPa	σ_y/MPa	σ_b/MPa	δ/%
in-situ TiB₂/7050	73.21	657.53	719.75	6.35
7050-Al	70.27	500.43	593.48	10.93
Note: E, elastic modulus; σ_y, yield strength; σ_b, ultimate strength; δ, elongation.

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表 2 环槽缺口圆棒试样分组信息

Table 2. Sets of the notched round bar specimens

R /mm	D /mm	K_t
0.2	6	2.53
1.0	6	1.77
3.0	6	1.37
Note：R, notch root radius; D, diameter of minimum section; K_t, stress concentration factor.

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表 3 成组法疲劳试验结果分析(R=0.1)

Table 3. Statistics results of fatigue life by grouping method (R=0.1)

Material	${\sigma _{{\text{max}}}}$/MPa	N_et	$\overline N $/Cycle	S	Cov/%
in-situ TiB₂/ 7050	530	4	19376	0.134	3.12
	500	4	34545	0.081	1.79
	470	5	40440	0.107	2.32
	440	4	95806	0.154	3.09
7050-Al	400	3	23543	0.058	1.33
	370	6	98418	0.195	3.92
	340	4	175461	0.099	1.89
	320	3	1742584	0.133	2.14
Note: N_et, number of effective tests; $\overline N $, Log. mean life; S, standard deviation; Cov, dispersion coefficients.

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表 4 成组法疲劳试验结果分析(R=0.5)

Table 4. Statistics results of fatigue life by grouping method (R=0.5)

Material	${\sigma _{{\text{max}}}}$/MPa	N_et	$\overline N $/Cycle	S	Cov/%
in-situ TiB₂/ 7050	530	3	43931	0.040	0.86
	500	3	88728	0.058	1.18
	470	5	100643	0.159	3.17
	450	3	4075838	0.111	1.68
7050-Al	500	4	34343	0.054	1.18
	450	3	62569	0.088	1.84
	430	3	94361	0.096	1.93
	410	3	795591	0.060	1.02

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表 5 升降法疲劳极限结果分析

Table 5. The fatigue limit obtained by up-down method

Material	R_s	N_ep	${{\text{σ }}_{\text{f}}}$/MPa	S/MPa	Cov/%
in-situ TiB₂/ 7050	0.1	6	380	10.95	2.88
in-situ TiB₂/ 7050	0.5	6	446.67	16.33	3.66
7050-Al	0.1	4	305	10	3.28
7050-Al	0.5	6	393.33	7.53	1.91
Note: N_ep, number of effective matched pairs; ${{\text{σ }}_{\text{f}}}$, fatigue limit; S, standard deviation; Cov, dispersion coefficients.

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表 6 in-situ TiB₂/7050和7050-Al S-N曲线参数

Table 6. Equation parameters of the fitted S-N curves of in-situ TiB₂/7050 and 7050-Al

Material	R_s	a	b	c
in-situ TiB₂/7050	0.1	380.28	4.6306×10⁻⁶	−0.13448
in-situ TiB₂/7050	0.5	446.43	1.0202×10⁻⁵	−0.17071
7050-Al	0.1	309.13	1.0565×10⁻⁶	−0.06955
7050-Al	0.5	401.79	1.5637×10⁻⁵	−0.24802

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表 7 成组法环槽缺口圆棒疲劳试验结果分析(R=0.1)

Table 7. The statistics analysis of fatigue life from notched round bar specimens by grouping method (R=0.1)

Material	K_t	$\mathop {\text{σ }}\nolimits_{{\text{max}}}^{{\text{notch}}} $/MPa	N_et	$\overline N $ /Cycle	S	Cov /%
in-situ TiB₂/7050	1.37	340	4	73292	0.124	2.87
		360	3	43990	0.087	1.88
		380	4	22079	0.152	3.13
	1.77	220	4	29680	0.088	2.33
		260	4	17564	0.105	2.47
		320	3	5820	0.030	0.68
	2.53	120	4	128424	0.132	2.90
	2.53	160	4	34241	0.138	2.70
7050-Al	1.37	320	8	31409	0.242	5.38
		360	3	25044	0.087	1.98
		400	4	9902	0.116	2.90
	1.77	220	3	32184	0.043	1.07
	1.77	280	3	9793	0.039	0.87
	2.53	120	3	74996	0.026	0.58
	2.53	170	3	34097	0.090	1.84

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