| 挤压式低室压推力室再生冷却问题 |
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| 引用本文： | 徐辉,林庆国,汪允武,张中光.挤压式低室压推力室再生冷却问题[J].火箭推进,2006,32(6):12-15. |
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| 作者姓名： | 徐辉 林庆国 汪允武 张中光 |
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| 作者单位： | 上海航天动力机械研究所,上海,200233 |
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| 摘 要： | 推力室冷却设计是液体火箭发动机设计的关键之一,通过论述推力10kN挤压式低室压推力室的冷却设计,对其进行了传热分析,并进行了试验验证。结果表明,推力室采用再生冷却和辐射冷却相结合的冷却方式时,发动机工作可靠,不会出现内壁烧蚀。
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| 关 键 词： | 液体火箭发动机 再生冷却 低室压 传热计算 热试车 |
| 文章编号： | (2006)06-0012-04 |
| 收稿时间： | 2005-09-27 |
| 修稿时间： | 2006-07-13 |
Regenerative cooling of the pressure-fed thruster with low-pressure chamber |
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| Xu Hui,Lin Qingguo,Wang Yunwu,Zhang Zhongguang.Regenerative cooling of the pressure-fed thruster with low-pressure chamber[J].Journal of Rocket Propulsion,2006,32(6):12-15. |
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| Authors: | Xu Hui Lin Qingguo Wang Yunwu Zhang Zhongguang |
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| Abstract: | The cooling of thruster chamber is one of important factors to design a liquid rocket thruster. This paper presents cooling design, heat transfer analysis and test verification of a pressure-fed thruster with low pressure chamber. Finally, we concluded that the thruster could run very well with no ablation if both regenerative cooling and radiation cooling are used at the same time. |
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| Keywords: | liquid rocket thruster regenerative cooling low-pressure chamber heat transfer simulation hot-fire test |
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