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| 固体/液体火箭发动机环境下3D C/SiC喉衬烧蚀性能实验 | |
| 引用本文： | 王文彬,李江,魏祥庚,董昊. 固体/液体火箭发动机环境下3D C/SiC喉衬烧蚀性能实验[J]. 西北工业大学学报, 2011, 29(4): 598-602 |
| 作者姓名： | 王文彬 李江 魏祥庚 董昊 |
| 作者单位： | 西北工业大学燃烧、热结构与内流场重点实验室,陕西西安,710072 |
| 摘 要： | 分别使用固体和液体火箭发动机实验系统对C/SiC陶瓷基复合材料的烧蚀性能进行了考核实验,主要研究了烧蚀时间、粒子和温度对材料烧蚀性能的影响。实验结果表明:随着烧蚀时间加长,材料烧蚀性能有明显下降趋势;温度高于2 973 K时,烧蚀明显加剧,且温度越高烧蚀越严重;强氧化燃气环境下,大量的H2O加剧了材料的热化学烧蚀。 |
| 关 键 词： | 火箭发动机 烧蚀 C/SiC复合材料 |
Experimentally Studying Ablation Properties of 3D C/SiC Throat-Insert for Solid Rocket Motor or Liquid Rocket Engine |
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| Wang Wenbin,Li Jiang,Wei Xianggeng,Dong Hao. Experimentally Studying Ablation Properties of 3D C/SiC Throat-Insert for Solid Rocket Motor or Liquid Rocket Engine[J]. Journal of Northwestern Polytechnical University, 2011, 29(4): 598-602 | |
| Authors: | Wang Wenbin Li Jiang Wei Xianggeng Dong Hao |
| Affiliation: | Science and Technology on Combustion,Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University,Xi′an 710072,China |
| Abstract: | Sections 1 and 2 of the full paper explain our experimental study.Their core consists of:(1)Fig.1 shows the sketch of our experimental setup of oxygen/alcohol gas generator;(2)subsection 1.2 is entitled experimental parameters;(3)Table 1 presents the results of 3D C/SiC ablation experiments for different lengths of ablation time;the analysis of these results shows that the ablative performance decays with longer ablation time;this analysis also shows that the ablation becomes acute when the temperature is h... |
| Keywords: | ablation rocket engines solid propellants liquid propellants composite materials C/SiC |
| 本文献已被 CNKI 万方数据 等数据库收录！ | |