Effect of ablation time on ablation mechanism of C/C-SiC composites in hypersonic and oxygen-enriched environment
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摘要: 为了研究烧蚀时间对C/C-SiC复合材料在高超声速富氧环境下烧蚀机制的影响规律，采用富氧环境下的高超声速烧蚀试验技术，对“化学气相渗透+先驱体浸渍裂解”混合工艺制备的针刺C/C-SiC复合材料动态烧蚀机制进行研究，并采用电子扫描显微镜观察烧蚀表面形貌。研究表明：在极端苛刻的高超声速富氧烧蚀环境下，C/C-SiC复合材料能够短时抵抗高温、高压、高超声速燃气射流的氧化工作环境。材料经高超声速富氧烧蚀10 s、20 s、30 s、40 s及50 s后的质量烧蚀率分别为0.021 g/s、0.025 g/s、0.027 g/s、0.026 g/s与0.034 g/s。C/C-SiC复合材料在高超声速富氧环境下的动态烧蚀行为主要受热化学烧蚀与机械剥蚀两种烧蚀机制共同作用。在初始阶段，SiO2保护膜的存在有效阻止了氧化性组分向基体内部的扩散，仅材料中心区域存在轻微热化学烧蚀；烧蚀试验中期，材料的烧蚀主要表现为热化学烧蚀与机械剥蚀联合作用，并由热化学烧蚀向机械剥蚀呈渐变性转变；烧蚀试验后期，基体的深度反应使得材料的烧蚀主要表现为纤维与基体的大面积片状剥落。
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关键词:
- C/C-SiC复合材料 /
- 高超声速 /
- 富氧烧蚀 /
- 烧蚀时间 /
- 烧蚀机制
Abstract: In order to study the effect of ablation time on the ablation mechanism of C/C-SiC composites under a hypersonic oxygen-rich environment, the dynamic ablation mechanism of the needled carbon/carbon-silicon carbide composites prepared by “chemical vapor infiltration + precursor immersion pyrolysis” hybrid process was studied by the hypersonic oxygen-enriched ablation test technology in this paper, and the ablation surface morphology of the composites were investigated by scanning electron microscopy. The results show that, the C/C-SiC composites can resist the oxidation working environment of high temperature, high pressure and hypersonic gas jets in a short time under the extremely harsh hypersonic oxygen-enriched ablation environment. The mass ablation rate of C/C-SiC composites after 10 s, 20 s, 30 s, 40 s and 50 s ablation by hypersonic oxygen-enriched ablation are 0.021 g/s, 0.025 g/s, 0.027 g/s, 0.026 g/s and 0.034 g/s, respectively. The dynamic ablation behavior of the C/C-SiC composites under the hypersonic oxygen-enriched environment is synergistic effects of thermo-oxidation ablation and mechanical erosion. In the initial stage, the existence of the SiO2 protective film effectively prevents the diffusion of oxidizing components into the matrix, and only the central area of the material is slightly thermal oxidative ablation. In the middle test, the ablation of the material is mainly manifested in the combined effect of thermo-oxidation ablation and mechanical erosion, and gradually transition from mainly thermal oxidative ablation to mainly mechanical erosion. In the later stage of the ablation test, the further reaction of the matrix makes the ablation mechanism of the material mainly manifested as the large-area flaking of the fiber and matrix.-
Key words:
- C/C-SiC composites /
- hypersonic /
- oxygen-enriched ablation /
- ablation time /
- ablation mechanism
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图 2 高超声速富氧环境烧蚀试验系统
Figure 2. Ablation test system of hypersonic oxygen-enriched environment
图 3 高压燃气发生器流场结构几何模型
Figure 3. Geometric model of flow field structure of high pressure gas generator
图 4 高压燃气发生器燃气射流温度分布
Figure 4. Temperature distribution of gas jet in high pressure gas generator
图 5 高压燃气发生器燃气射流速度分布
Figure 5. Velocity distribution of gas jet in high pressure gas generator
图 6 C/C-SiC复合材料在高超声速富氧烧蚀环境下不同时刻的动态烧蚀形貌
Figure 6. Dynamic ablation morphologies of C/C-SiC composites at different moments in hypersonic oxygen-enriched ablation environment
图 7 C/C-SiC复合材料在不同烧蚀时刻的微观形貌：((a)、(b)) 烧蚀10 s后的微观形貌；((c)、(d)) 烧蚀20 s后的微观形貌；((e)、(f)) 烧蚀30 s后的微观形貌；((g)、(h)) 烧蚀40 s后的微观形貌；((i)、(j)) 烧蚀50 s后的微观形貌
Figure 7. Micro-morphologies of C/C-SiC composites at different ablation moments: ((a), (b)) Micro-morphologies after 10 s ablation; ((c), (d)) Micro-morphology after 20 s ablation; ((e), (f)) Micro-morphologies after 30 s ablation; ((g), (h)) Micro-morphologies after 40 s ablation; ((i), (j)) Micro-morphologies after 50 s ablation
图 8 C/C-SiC复合材料轴向与径向纤维在不同烧蚀时刻的微观形貌：((a)、(b)) 烧蚀10 s后的轴向与径向纤维；((c)、(d)) 烧蚀20 s后的轴向与径向纤维；((e)、(f)) 烧蚀30 s后的轴向与径向纤维；((g)、(h)) 烧蚀40 s后的轴向与径向纤维；((i)、(j)) 烧蚀50 s后的轴向与径向纤维
Figure 8. Microscopic morphology for axial and radial fibers of C/C-SiC composites at different ablation time: ((a), (b)) Axial and radial fibers after 10 s ablation; ((c), (d)) Axial and radial fibers after 20 s ablation; ((e), (f)) Axial and radial fibers after 30 s ablation; ((g), (h)) Axial and radial fibers after 40 s ablation; ((i), (j)) Axial and radial fibers after 50s ablation
图 9 C/C-SiC复合材料烧蚀后材料内部的氧化活性点
Figure 9. Oxidation active sites inside the C/C-SiC composites after ablation
表 1 C/C-SiC复合材料在极端苛刻高超声速富氧环境下的烧蚀试验参数
Table 1. Ablation test parameters of C/C-SiC composites in extremely harsh hypersonic oxygen-enriched environment
Sample Flow of kerosene/
(kg·min−1)Flow of
oxygen/SLMOxygen enrichment
degree/vol%Combustion chamber
pressure/MPaDistance/mm Time/s 1# 0.2 500 5.0 1.00 80 10 2# 0.2 500 5.0 1.00 80 20 3# 0.2 500 5.0 1.00 80 30 4# 0.2 500 5.0 1.00 80 40 5# 0.2 500 5.0 1.00 80 50 Note: SLM—Standard liters per minute. 
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表 2 针刺C/C-SiC复合材料性能
Table 2. Properties of needle punched C/C-SiC composites
Density/
(g·cm−3)Thermal
conductivity/
(W·m−1·K−1)Compressive
strength/
MPaIn-plane shear
strength/
MPaBending
strength/
MPaTime/s Mass ablation
rate/(g·s−1)Rate of change
in mass ablation
rate/%1.85 10.21 205 18.7 180 10 0.021(~10 s) — 20 0.025(10-20 s) 20.24 30 0.027(20-30 s) 10.83 40 0.026(30-40 s) 5.32 50 0.034(40-50 s) 30.00
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