| 液体火箭发动机自引射工作过程传热研究 |
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| 引用本文： | 张忠利,周立新,张蒙正.液体火箭发动机自引射工作过程传热研究[J].火箭推进,2012(1):31-37. |
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| 作者姓名： | 张忠利 周立新 张蒙正 |
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| 作者单位： | 西安航天动力研究所,陕西西安710100 |
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| 基金项目： | 中国航天科技集团公司支撑项目 |
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| 摘 要： | 建立了液体火箭发动机自引射工作过程传热分析模型。分析了圆柱型和二次喉道型引射器在不同冷却水流量下引射器的壁温和热流的变化,得到了引射器可靠工作的冷却水流量范围,引射器冷却水温升测试值和仿真值的一致性较好。
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| 关 键 词： | 液体火箭发动机 引射器 传热 |
Investigation on heat transfer characteristics of LRE self-ejecting process |
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| ZHANG Zhong-li,ZHOU Li-xin,ZHANG Meng-zheng.Investigation on heat transfer characteristics of LRE self-ejecting process[J].Journal of Rocket Propulsion,2012(1):31-37. |
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| Authors: | ZHANG Zhong-li ZHOU Li-xin ZHANG Meng-zheng |
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| Institution: | (Xi＇ an Aerospace Propulsion Institute, Xian 710100, China) |
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| Abstract: | An analytical model for convective and radiate heat transfer between the hot gas and the ejector structure was established. The variation of wall temperature and heat flow of the cylindri- cal and secondary-throat ejectors in the case of different cooling water flow is analyzed. The range of mass flow rate of the cooling water needed for heat protection of the ejector was determined on the basis of detailed heat transfer analysis. The computational results show that the simulation results are consistent with the experimental measurements obtained in the vacuum cabin. |
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| Keywords: | liquid rocket engine ejector heat transfer |
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