Study on tensile properties of SiCf/TC17 composites and strength analysis of blade-ring structure
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摘要:
对SiCf/TC17复合材料开展室/高温纵向拉伸试验，研究不同温度的拉伸性能，通过断口形貌分析阐释断裂机制，建立本构模型描述其拉伸行为。结果表明：SiCf/TC17的断裂强度随着温度升高而降低，同时应力应变曲线的非线性段增加；室温（25 ℃）的断裂机制主要是反应层断裂和纤维随机断裂，而高温下出现大规模的纤维拔出与界面脱黏、基体韧性断裂和多纤维断裂；不同强度预测模型的结果表明：25 ℃下材料的断裂模式以局部承担载荷为主，而高温更符合全局承担模型；所提出的耦合纤维累积损伤的本构模型很好地模拟了25 ℃和450 ℃的应力应变曲线。最后基于试验所得拉伸性能，开展了叶环结构的应力应变分析和静强度校核，在典型服役温度下，叶环结构具有较高的强度储备系数。
Abstract:Longitudinal tensile tests were carried out on SiCf/TC17 composites at room/high temperature to investigate the tensile behaviors. The damage evolution and failure mechanisms were revealed based on microscopic fracture morphology analysis. Afterwards, a constitutive model was developed to describe the tensile behaviors of SiCf/TC17 composites. The results showed that the ultimate tensile strength of SiCf/TC17 composites decreased with the increasing temperature, while the nonlinear segment of the stress-strain curve increased. The major failure mechanisms at room temperature (25 ℃) lied in multiple fractures of the interfacial reaction layer and random breakage of weak fibers, whereas large-scale interface debonding and fiber pullout, matrix cracking and fiber breakage were more common at high temperatures. The results of different strength-predicted models demonstrated that the failure mode of SiCf/TC17 composites at 25 ℃ was controlled by local loading sharing, while the high-temperature ultimate tensile strength was more consistent with the global loading sharing model. The stress-strain curve of SiCf/TC17 composites was simulated by the proposed constitutive model with coupling fiber cumulative damage. The simulation results exhibited a trend similar to that of the experimental data at 25 ℃ and 450 ℃. Finally, based on the tensile properties obtained from the tests, finite element stress-strain analysis and static strength calibration of the TMCs blade-ring structure were carried out. The result indicated that the blade-ring structure exhibited a significantly elevated strength reserve factor at the typical service temperature.
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图 3 SiCf/TC17复合材料及TC17基体的应力-应变曲线
Figure 3. Stress-strain curves of SiCf/TC17 composites and TC17 matrix
图 4 SiCf/TC17复合材料25 ℃拉伸断口SEM形貌
Figure 4. Tensile fracture morphology of SiCf/TC17 composites observed by SEM at 25 ℃
图 5 SiCf/TC17复合材料25 ℃拉伸断口X-CT形貌
Figure 5. Tensile fracture morphology of SiCf/TC17 composites captured by X-CT at 25 ℃
图 6 SiCf/TC17复合材料450 ℃拉伸断口SEM形貌
Figure 6. Tensile fracture morphology of SiCf/TC17 composites observed by SEM at 450 ℃
图 7 SiCf/TC17复合材料650 ℃拉伸断口SEM形貌
Figure 7. Tensile fracture morphology of SiCf/TC17 composites observed by SEM at 650 ℃
图 8 SiCf/TC17复合材料拉伸断裂强度的模型预测结果
Figure 8. Predicted results of ultimate tensile strength of SiCf/TC17 composites
图 9 TMCs本构模型的架构图和实现流程
Figure 9. Architecture and implementation of the proposed constitutive model for TMCs
图 11 TMCs在450 ℃下的应力-应变曲线模拟结果
Figure 11. Simulated stress-strain curves of TMCs at 450 ℃
表 1 TMCs和TC17合金的拉伸性能
Table 1. Tensile properties of TMCs and TC17 alloy
材料 温度/℃ 弹性模量/GPa 屈服强度/MPa 断裂强度/MPa 断裂应变/% 屈强比 SiCf/TC17 25 208 1782 1923 0.94 0.93 SiCf/TC17 450 200±6 1177 ±71449 ±160.78±0.01 0.81 SiCf/TC17 650 178 624 975 0.61 0.64 TC17 25 113 959 1059 >8.00 0.91 TC17 450 77 613 726 >8.00 0.84 TC17 650 31 197 228 >8.00 0.86 
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表 2 SiCf/TC17复合材料拉伸断裂强度的模型预测误差
Table 2. Predicted error of ultimate tensile strength of SiCf/TC17 composites
试验温度/℃ 相对误差/% 试验 ROM GLS LLS，i = 1 LLS，i = 2 LLS，i = 3 LLS，i = 4 25 0 3.48 9.62 −32.55 −10.09 1.46 8.58 450 0 22.22 1.31 −41.89 −17.87 −5.25 2.69 650 0 47.90 0.31 −44.82 −18.15 −3.49 5.85
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表 3 压气机叶环构件的强度安全系数
Table 3. Safety factors for strength of compressor blade-ring components
应力部位及类型 TMCs TC17 ns nb ns nb 最大径向应力 1.25 1.54 1.25 1.54 平均周向应力 1.25 1.54 1.25 1.54 环内径周向应力 1.05
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表 4 TMCs叶环结构的应力和强度储备系数
Table 4. Stress and strength reserve factors of blade-ring structures of TMCs
应力部位及类型 参数 TMCs TC17 ns nb ns nb 最大径向应力 应力值/MPa 74 74 142 142 强度系数 2.03 2.70 4.32 5.11 平均周向应力 应力值/MPa 1113 1113 334 334 强度系数 1.31 1.61 1.84 2.17 环内径周向应力 应力值/MPa 424 强度系数 1.45
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