钛合金典型结构细节原始疲劳质量分析

刘潇然; 孙秦

doi:10.13433/j.cnki.1003-8728.20200112

钛合金典型结构细节原始疲劳质量分析

doi: 10.13433/j.cnki.1003-8728.20200112

刘潇然^1,,
孙秦^2, ,

1.
郑州航空工业管理学院航空工程学院, 郑州 450046
2.
西北工业大学航空学院, 西安 710072

基金项目:

国家自然科学基金项目 51375386

详细信息

作者简介:
刘潇然(1990-), 讲师, 博士, 研究方向为飞行器结构精细化设计, 285962796@qq.com

通讯作者:
孙秦, 教授, 博士生导师, sunqin@nwpu.edu.cn

中图分类号: V215.5⁺²
计量
- 文章访问数: 114
- HTML全文浏览量: 26
- PDF下载量: 16
- 被引次数: 0
出版历程
- 收稿日期: 2019-12-05
- 刊出日期: 2021-05-01

Analysis of Initial Fatigue Quality for Representative Structure Detail of TC4

LIU Xiaoran^1
,,
SUN Qin^{2
, ,}

1.
School of Aeronautical Engineering, Zhengzhou University of Aeronautics, Zhengzhou 450046, China
2.
School of Aeronautics, Northwestern Polytechnical University, Xi′an 710072, China

摘要

摘要: 针对飞机结构中常用的钛合金典型结构细节，采用原始疲劳质量方法对其耐久性进行了分析。首先完成了钛合金典型结构细节在3个应力水平下的耐久性试验，通过疲劳断口判读补充了小裂纹扩展数据集，统计获得了各应力水平下的裂纹形成时间TTCI及通用当量初始缺陷尺寸EIFS的概率分布及特征参数。在此基础上，预测了典型结构细节95%可靠度疲劳寿命，并基于EIFS分布预测了95%可靠度的当量初始裂纹尺寸，结果表明该钛合金典型结构细节满足设计要求。
- 钛合金 /
- 原始疲劳质量 /
- 耐久性 /
- 裂纹形成时间 /
- 当量初始缺陷尺寸
Abstract: For the representative structure detail of titanium alloy applied in aeronautical engineering structure, the durability is analyzed by using the initial fatigue quality method. The durability tests of the representative structure detail of titanium alloy under 3 stress levels are performed on Instron8802 test machine. The crack growth data of the representative structure detail is obtained by analyzing the fracture via electron microscope. The probabilistic characteristics for the time of crack initiation (TTCI) and equivalent initial flaw size (EIFS) are achieved with the statistical analysis of test data. Then, the 95% reliability fatigue life is predicted via initial fatigue quality method. Besides, the 95% reliability EIFS is also calculated based on EIFS distribution. Results show that the representative structure detail of titanium alloy meets the requirement of durability design.
- titanium alloy /
- initial fatigue quality /
- durability /
- crack initiation time /
- equivalent initial flaw size

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图 1 单片双孔耐久性试件

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图 2 耐久性疲劳试验中的小裂纹检测照片

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图 3 疲劳条带标识图

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图 4 各应力水平下的a-t曲线

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图 5 通用EIFS分布原理图

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图 6 通用EIFS分布建立流程图

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表 1 3组试验应力水平

高应力/MPa	中应力/MPa	低应力/MPa
485.419	463.355	441.290

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表 2 给定参考裂纹尺寸a_r下计算出的TTCI数据表(中应力)

断口编号	TTCI(k)/fh
断口编号	a_r=0.35 mm	a_r=0.65 mm	a_r=0.95 mm	a_r=1.25 mm	a_r=1.55 mm	a_r=1.85 mm	a_r=2.15 mm
1(31020)	19 746.22	20 013.35	20 501.79	20 762.54	21 004.15	21 138.19	21 413.49
2(31021)	12 673.61	13 575.11	13 972.85	14 455.69	14 952.70	15 309.42	15 632.05
3(31022)	11 534.79	12 362.99	12 766.88	13 631.23	14 364.82	14 931.95	15 473.45
4(31023)	20 369.55	21 463.12	22 052.39	22 560.80	23 383.33	23 550.87	23 775.01
5(31024)	12 560.46	14 125.69	14 685.94	14 862.04	15 446.96	15 810.33	15 991.27
TTCI均值	15 376.93	16 308.05	16 795.97	17 254.46	17 830.39	18 148.15	18 457.05

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表 3 3组应力水平下TTCI分布参数

σ/MPa	Q	α	β	ε
485.419	5.347×10^-4	4.205	13 279.402	1 251.896
463.355	5.828×10^-4	3.247	18 093.428	1 148.678
441.290	3.093×10^-4	3.213	20 842.969	2 164.387

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表 4 优化后通用EIFS分布参数

a_r	x_u	α	Qβ
0.89	0.78	4.259 5	6.906 5

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表 5 预测寿命结果

a_r/mm	σ/MPa	T_R/fh	T_MIN/fh	T_AVE/fh
	485.419	5 398.91	10 150.68	12 084.42
0.65	463.355	7 071.76	12 362.99	16 308.05
	441.290	9 385.87	12 929.07	18 649.93
	485.419	6 483.02	10 718.89	13 355.05
1.25	463.355	8 491.78	13 631.23	17 254.46
	441.290	11 270.57	14 049.53	20 735.20
	485.419	7 132.97	10 937.23	14 095.52
1.85	463.355	9 343.11	14 931.95	18 148.15
	441.290	12 400.49	15 205.25	22 135.03

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