考虑分层损伤的平纹编织SiC/SiC带孔板-金属销钉连接结构失效分析

陈强; 张盛; 冯雨春; 高希光; 宋迎东

doi:10.13224/j.cnki.jasp.20230567

考虑分层损伤的平纹编织SiC/SiC带孔板-金属销钉连接结构失效分析

doi: 10.13224/j.cnki.jasp.20230567

陈强^1,,
张盛^1,*, ,,
冯雨春¹,
高希光¹,
宋迎东^{1, 2}

1.
南京航空航天大学能源与动力学院航空发动机热环境与热结构工业和信息化部重点实验室，南京 210016
2.
南京航空航天大学航空航天结构力学及控制全国重点实验室，南京 210016

基金项目: 国家自然科学基金（11972183，52202098）

详细信息

作者简介:
陈强（1997-），男，硕士生，主要从事航空发动机结构强度研究。E-mail：nuaa_cepe_cq@nuaa.edu.cn

通讯作者:
张盛（1990-），男，副研究员，博士，主要从事航空发动机结构强度研究。E-mail：zhangsheng@nuaa.edu.cn

中图分类号: V231.9
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- 文章访问数: 389
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- 被引次数: 0
出版历程
- 收稿日期: 2023-09-05
- 网络出版日期: 2024-06-18

Failure analysis of plain woven SiC/SiC perforated plate-metal pin connection structure considering delamination damage

1.
Key Laboratory of Aero-Engine Thermal Environment and Structure，Ministry of Industry and Information Technology，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
State Key Laboratory of Mechanics and Control of Aerospace Structures，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
为探究陶瓷基复合材料（CMC）机械连接结构在航空发动机中的应用潜力，采用试验与数值模拟相结合的方法研究了平纹编织SiC/SiC带孔板-金属销钉连接结构在拉伸状态下的失效模式与破坏过程，并通过数字图像相关（DIC）技术实时观测试件变形与失效过程。试验结果表明：结合分层损伤的剪切破坏是连接结构主要的失效形式。基于内聚力模型（CZM），使用渐进损伤分析方法（PDA）预测了平纹编织SiC/SiC带孔板的失效载荷、失效模式及分层损伤，预测结果与试验结果吻合，失效载荷预测误差小于10%，表明了数值模型对结构失效分析的有效性。
- 平纹编织SiC/SiC /
- 连接结构 /
- 内聚力模型 /
- 渐进损伤分析 /
- 分层损伤
Abstract:
To explore the application potential of ceramic matrix composite (CMC) mechanical connection structure in aero-engine, the failure mode and failure process of plain woven SiC/SiC perforated plate-metal pin connection structure under tension state were studied by combining test and numerical simulation. The deformation and failure process of the test specimens in real-time were observed through digital image correlation (DIC) technology. The main failure mode of the connected structure arising from the shear failure combined with delamination damage was revealed by test results. Based on the cohesive zone model (CZM), the failure load, failure mode and delamination damage of the plain woven SiC/SiC perforated plate were predicted by using the progressive damage analysis method (PDA). Good consistency between the numerical failure predictions and the test results was obtained, and the failure load prediction error was less than 10%, indicating the validity of the numerical model for the failure analysis of connection structure.
- plain woven SiC/SiC /
- connection structure /
- cohesive zone model /
- progressive damage analysis /
- delamination damage

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图 1 平纹编织SiC/SiC带孔板-金属销钉连接结构模型（单位：mm）

Figure 1. Plain woven SiC/SiC perforated plate -metal pin connection structure model (unit：mm)

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图 2 平纹编织SiC/SiC带孔板试件示意图

Figure 2. Plain woven SiC/SiC perforated plate specimen configuration

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图 3 DIC及拉伸试验设备

Figure 3. DIC and tensile test equipment configuration

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图 4 平纹编织SiC/SiC带孔板-金属销钉连接结构有限元模型

Figure 4. Finite element model of plain woven SiC/SiC perforated plate-metal pin connection structure

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图 5 双线性张力-位移本构关系及损伤演化示意图

Figure 5. Bilinear traction-separation law and damage evolution schematic diagram

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图 6 平纹编织SiC/SiC复合材料应力-应变曲线

Figure 6. Plain woven SiC/SiC composite stress-strain curves

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图 7 SiC/SiC复合材料连接结构渐进损伤分析流程图

Figure 7. Flowchart for progressive damage analysis of SiC/SiC composite connection structure

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图 8 CMC带孔板-金属销钉连接结构拉伸试验载荷-位移曲线

Figure 8. Load-displacement curves of CMC perforated plate-metal pin connection structure tensile test

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图 9 CMC带孔板DIC-ε_yy应变云图

Figure 9. DIC- ε_yy strain contour plots of CMC perforated plate

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图 10 CMC带孔板失效模式

Figure 10. Failure pattern of CMC perforated plate

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图 11 不同接触设置下的载荷-位移曲线

Figure 11. Load-displacement curves with different contact settings

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图 12 CMC带孔板失效过程有限元模拟

Figure 12. Finite element simulation of failure process of CMC perforated plate

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图 13 CMC带孔板分层损伤演化过程

Figure 13. Delamination damage propagation process of the CMC perforated plate

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图 14 试验结果与有限元失效分析结果比较

Figure 14. Comparison of test result and FEA failure analysis

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图 15 DIC应变场分布与有限元仿真分析结果对比

Figure 15. Comparison of DIC strain dsitribution and FEA simulation analysis

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表 1 SiC/SiC材料参数^[14-16]

Table 1. Material properties of SiC/SiC^[14-16]

参数	数值	参数	数值
（E₁= E₂）/GPa	227.40	（X_t= Y_t）/MPa	224.98
E₃/GPa	50.00	（X_c= Y_c）/MPa	603.66
G₁₂/GPa	91.00	S₁₂/MPa	176.19
（G₁₃= G₂₃）/GPa	17.70	（S₁₃=S₂₃）/MPa	40.02
${\nu _{12}}$	0.15	${\nu _{13}} = {\nu _{23}}$	0.25

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表 2 GH4169材料参数^[17]

Table 2. Material properties of GH4169^[17]

参数	数值
E/GPa	204
G/GPa	79
$\nu $	0.3

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表 3 CZM参数^[26-28]

Table 3. CZM parameters^[26-28]

模型	参数	数值
Mode Ⅰ	强度极限${\sigma _{{\text{max}}}}/{\mathrm{MPa}}$	15
Mode Ⅰ	临界断裂能G_Ⅰc/（J/m²）	400
Mode Ⅱ	剪切强度极限${\tau _{{\text{max}}}}/{\mathrm{MPa}}$	40
Mode Ⅱ	临界断裂能G_Ⅱc/（J/m²）	500

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表 4 突降退化模型参数

Table 4. Paramaters of sudden degradation model

失效模式	材料参数退化规则
经纱方向拉伸/压缩	$\left[ {{E_1},{G_{12}},{G_{13}},{\nu _{12}},{\nu _{13}}} \right] \times 0.2$
纬纱方向拉伸/压缩	$\left[ {{E_2},{G_{12}},{G_{23}},{\nu _{12}},{\nu _{23}}} \right] \times 0.2$
层间拉伸/压缩	$\left[ {{E_3},{G_{13}},{G_{23}},{\nu _{13}},{\nu _{23}}} \right] \times 0.2$

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表 5 试验与仿真结构的载荷峰值比较

Table 5. Comparison of peak load results between test and simulation

载荷峰值/N			模拟结果峰值/N			误差/%
试件1	试件2	平均值	CZM 模拟	Bonded模拟	平均值	CZM模拟	Bonded模拟
4025.26	3718.72	3872.00	3 757.99	4723.90	3872.00	−2.94	22.00

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