TC6 钛合金的率相关力学模型研究

张海洋; 李鑫; 蔚夺魁; 王相平; 任磊; 张超

doi:10.13224/j.cnki.jasp.20240072

TC6 钛合金的率相关力学模型研究

doi: 10.13224/j.cnki.jasp.20240072

张海洋^{1, 2, 3, 4,},
李鑫⁵,
蔚夺魁^{2, 4},
王相平^{2, 3},
任磊⁶,
张超^{1, 3, 5,*, ,}

1.
西北工业大学民航学院，西安 710072
2.
中国航发沈阳发动机研究所，沈阳 110015
3.
中国航发沈阳发动机研究所辽宁省航空发动机冲击动力学重点实验室，沈阳 110015
4.
太行实验室辽宁研究中心，沈阳 110015
5.
西北工业大学航空学院，西安 710072
6.
北京三翼志航科技有限公司，北京 100020

详细信息

作者简介:
张海洋（1988-），男，高级工程师，博士，主要从事航空发动机结构强度研究

通讯作者:
张超（1987-），男，教授，博士，主要从事固体力学、复合材料研究。E-mail：chaozhang@nwpu.edu.cn

中图分类号: V232
计量
- 文章访问数: 477
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- 被引次数: 0
出版历程
- 收稿日期: 2024-02-01
- 网络出版日期: 2025-09-24

Investigation on strain rate-dependent mechanical model for TC6 titanium alloy

ZHANG Haiyang^{1, 2, 3, 4
,},
LI Xin⁵,
YU Duokui^{2, 4},
WANG Xiangping^{2, 3},
REN Lei⁶,
ZHANG Chao^{1, 3, 5,*
, ,}

1.
School of Civil Aviation，Northwestern Polytechnical University，Xi’an 710072，China
2.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
3.
Key Laboratory of Impact Dynamics on Aero Engine，Liaoning Province，Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
4.
Taihang Laboratory Liaoning Base，Shenyang 110015，China
5.
School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China
6.
Beijing TRI-WING Technology Corporation，Beijing 100020，China

摘要

摘要:
为研究TC6钛合金材料的力学性能，使用电子万能试验机、高速拉伸试验机、分离式Hopkinson拉杆（SHTB）和压杆（SHPB）试验装置，开展了TC6钛合金材料的准静态及动态试验，获得了TC6钛合金材料不同应变率下真实应力-应变曲线及失效应变。采用线弹性本构模型描述材料的弹性力学行为，采用塑性应力-应变曲线表征材料的塑性力学行为，采用韧性断裂和剪切失效的竞争模式来表征材料的失效力学行为。基于试验结果，通过外推预测方法和数值仿真手段，校正了颈缩点后的应力-应变曲线、韧性断裂参数以及剪切失效参数。开展了低速落锤冲击试验和高速鸟撞叶片试验，进行了基于Pam Crash软件的试验状态仿真，通过试验与仿真结果对比，落锤试验中试验件裂纹长度误差为4.2%，高速鸟撞叶片试验中应变峰值最大误差为14.9%，验证了材料力学模型及其参数的有效性。
- TC6钛合金 /
- 力学性能 /
- 应变率效应 /
- 准静态试验 /
- 动态试验 /
- 试验数据校正
Abstract:
To investigate the mechanical properties of TC6 titanium alloy, quasi-static and dynamic tests were conducted using an electronic universal testing machine, a high-speed tensile testing machine, and split Hopkinson tensile bar (SHTB) and split Hopkinson pressure bar (SHPB) apparatus. These tests yielded the true stress-strain curves and failure strains of the TC6 titanium alloy at various strain rates. The elastic mechanical behavior of the material was described using a linear elastic model. The plastic mechanical behavior was characterized by plastic stress-strain curves. Additionally, a competition model involving ductile fracture and shear failure was employed to describe the failure mechanical behavior. Based on test results, the stress-strain curves after necking, the ductile fracture parameters and shear failure parameters were determined using extrapolation prediction methods and numerical simulations. Low-velocity drop hammer impact tests and high-speed bird impact on blades tests were conducted, along with simulations of the test conditions using Pam-Crash software. By comparing the test and simulation results, the error in crack length for the drop hammer test was found to be 4.2%, while the maximum error in peak strain for the high-speed bird impact on blades tests was 14.9%. These results validated the effectiveness of the material mechanical model and its parameters.
- TC6 titanium alloy /
- mechanical properties /
- strain rate effect /
- quasi-static tests /
- dynamic tests /
- test data calibration

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图 1 力学性能测试试样形状及尺寸（单位：mm）

Figure 1. Shape and dimension of test specimens for mechanical properties （unit：mm）

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图 2 力学性能测试试样

Figure 2. Test specimens for mechanical properties

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图 3 INSTRON万能拉伸试验机

Figure 3. INSTRON universal tensile testing machine

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图 4 TC6钛合金真实应力-真实应变曲线

Figure 4. True stress-true strain curves of TC6 titanium alloy

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图 5 准静态拉伸加载下的断裂拉伸试样

Figure 5. Fractured tensile specimen under quasi-static tensile loading

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图 6 动态试验测试设备

Figure 6. Dynamic mechanical testing equipment

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图 7 不同应变率下的断裂加载试样

Figure 7. Fracture tensile specimens at the different strain rates

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图 8 颈缩前应力-应变曲线确定过程示意图

Figure 8. Schematic diagram of the determination process for Pre-necking stress-strain curves

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图 9 所有加载工况的外推曲线簇

Figure 9. Extrapolation curves cluster for all loading conditions

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图 10 韧性断裂和剪切失效的图示

Figure 10. Illustration of ductile fracture and shear failure

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图 11 建立的准静态加载案例的数值模型

Figure 11. Established numerical model of the quasi-static loading case

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图 12 准静态加载工况的数值仿真与试验结果对比

Figure 12. Comparison between numerical simulation and test results under quasi-static loading conditions

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图 13 高应变率加载工况的有限元模型

Figure 13. Finite element model of the high strain rates loading cases

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图 14 TC6钛合金不同应变率下的塑性变形段应力-应变曲线

Figure 14. Stress-strain curves of TC6 titanium alloy during plastic deformation segment at different strain rates

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图 15 落锤低速冲击试验

Figure 15. Drop hammer low-speed impact test

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图 16 落锤低速冲击试验的冲击过程

Figure 16. Impact process of the drop hammer low-speed impact test

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图 17 TC6材料的落锤低速冲击试验的数值模型

Figure 17. Numerical model for the drop hammer low-speed impact test of TC6 material

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图 18 裂纹长度对比

Figure 18. Comparison of crack lengths

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图 19 鸟体高速撞击叶片试验的测试装置

Figure 19. Test equipment for high-speed bird impact on blades

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图 20 试验所用叶片实物及明胶鸟体实物

Figure 20. Blade and bird bullet used in test

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图 21 试验中鸟体撞击叶片过程

Figure 21. Process of bird impact on blades during testing

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图 22 叶片的损伤形貌

Figure 22. Damage morphology of the blade

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图 23 鸟体撞击叶片的数值模型

Figure 23. Numerical model of bird impact on blades

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图 24 数值仿真中鸟体撞击叶片过程

Figure 24. Process of bird impact on blades in numerical simulation

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表 1 TC6材料的材料参数

Table 1. Material parameters of TC6 material

密度/（g/cm³）	弹性模量/GPa	泊松比	剪切参数k_s
4.51	109.8	0.3	0.139

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表 2 TC6材料的失效参数汇总

Table 2. Summary of failure parameters for TC6 material

试验工况	拉伸失效参数g_d	剪切失效参数g_s
准静态	0.35	0.25
10 s⁻¹	0.55	0.5
100 s⁻¹	0.5	0.5
500 s⁻¹	0.22	0.22
1000 s⁻¹	0.7	0.7
2000 s⁻¹	0.58	0.58
5000 s⁻¹	0.62	0.62
10000 s⁻¹	0.6	0.6

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表 3 TC6材料的落锤低速冲击试验的数值模型中的接触设置

Table 3. Contact settings used in the numerical model for the drop hammer low-speed impact test of TC6 material

序号	接触类型	主接触面	从接触面
1	44号接触	支撑板	夹具
2	44号接触	夹具	试样
3	44号接触	夹具盖板	试样
4	44号接触	螺栓	夹具
5	44号接触	螺栓	试样
6	33号接触	摆锤	试样
7	44号接触	导杆	摆锤

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表 4 测量点位置

Table 4. Location of measurement point

编号	名称	位置
1	冲击中心	叶片顶端靠近前缘
2	应变片1、2	距顶部240 mm，距前缘25 mm， 1纵向排布，2横向排布
3	应变片3、4	距叶根80 mm，距前缘25 mm， 3纵向排布，4横向排布
4	应变片5、6	距叶根95 mm，距后缘25 mm， 5纵向排布，6横向排布
5	应变片7、8	距叶根20 mm，距前缘100 mm， 7纵向排布，8横向排布

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表 5 鸟撞试验测试结果

Table 5. Results of bird impact test

试验件	弹体质量/g	冲击速度/（m/s）	峰值应变/με
毛坯叶片	1522.9	208	1：45651
			2：11525
			3：12421
			4：9344
			5：10372
			6：14850
			7：17128
			8：18183

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表 6 鸟体材料参数

Table 6. Material parameter of the bird

密度/（g/cm³）	体积系数	γ
9.5	0.128	7.98

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表 7 试验与数值仿真结果对比

Table 7. Comparison between test and numerical simulation

项目	试验应变片峰值	模拟单元应变峰值	误差/%
应变片1	45651	39261	−13.9
应变片2	11525	10488	−8.9
应变片3	12421	10966	−11.7
应变片4	9344	10364	10.9
应变片5	10372	9108	−12.2
应变片6	14850	13959	−6.4
应变片7	17128	19763	14.9
应变片8	18183	17984	−1.1

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