双组元液体动力环境下3DC/SiC复合材料喷管烧蚀性能
Ablation performance of 3DC/SiC composite nozzles under double-component liquid power environment
查看参考文献20篇
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文摘
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为明确C/SiC陶瓷基复合材料喷管在液体火箭发动机工作环境的烧蚀特性,采用先驱体浸渍-裂解(PIP)工艺制备得到3DC/SiC复合材料喷管,并对喷管进行多种工况环境下的地面热试车烧蚀考核。结果表明:制备得到的3DC/ SiC复合材料喷管能够满足液体火箭发动机多种工况环境下抗烧蚀性能要求,喷管喉部线烧蚀率约为3.92×10~(-4)mm/s;热试车烧蚀实验后喷管入口圆柱段、收敛段、喉部及扩张段外型面均残留有大量白色物质SiO_2,喉部局部出现烧蚀坑洞现象;C/SiC复合材料液体火箭发动机工作环境下的烧蚀机理为机械冲刷烧蚀和氧化烧蚀。 |
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其他语种文摘
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In order to explore the ablation characteristics of C/SiC ceramic composite nozzles in the working environment of liquid rocket engines,3D C/SiC composite nozzle was prepared by the precursor impregnation pyrolysis(PIP)process,and the ablation test of the nozzle in various working conditions was carried out.The results show that 3D C/SiC composite nozzle can meet the requirements of anti-ablation performance of the liquid rocket engine under various working conditions.The wire ablation rate of nozzle throat is about 3.92×10~(-4)mm/s;after the hot test vehicle ablation test,a large amount of white matter SiO_2 remains on the inlet cylindrical section,convergent section,throat section and expansion section outer surface of the nozzle,and the ablation pit appears in the throat;the ablation mechanisms of C/SiC composites under liquid rocket engine are mainly mechanical erosion ablation and oxidation ablation. |
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来源
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材料工程
,2022,50(2):118-126 【核心库】
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DOI
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10.11868/j.issn.1001-4381.2020.000641
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关键词
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3DC/SiC复合材料
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喷管
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液体动力环境
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烧蚀性能
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烧蚀机理
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地址
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1.
西北工业大学, 西安, 710072
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西安航天动力研究所, 西安, 710010
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1001-4381 |
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学科
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一般工业技术 |
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基金
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国家自然科学基金
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文献收藏号
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CSCD:7201680
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