| 液体火箭发动机涡轮壳体温度偏高原因研究 |
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| 引用本文： | 张忠利,张蒙正,李福云. 液体火箭发动机涡轮壳体温度偏高原因研究[J]. 火箭推进, 2013, 39(2): 35-39 |
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| 作者姓名： | 张忠利 张蒙正 李福云 |
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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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| 摘 要： | 分析了液体火箭发动机001～003试车时发生器排气壳体和涡轮进排气壳体的温度变化情况。应用非稳态传热方法对实际结构仿真了003次试车时发生器在不同流量、不同效率时涡轮壳体温度的变化情况，得出了该次试车时涡轮壳体温度偏高的主要原因是发生器燃烧效率偏高。
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| 关 键 词： | 液体火箭发动机 涡轮 仿真计算 试车 |
Investigation on reason of overheating of turbine housing in liquid rocket engine |
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| ZHANG Zhong-li , ZHANG Meng-zheng , LI Fu-yun. Investigation on reason of overheating of turbine housing in liquid rocket engine[J]. Journal of Rocket Propulsion, 2013, 39(2): 35-39 |
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| Authors: | ZHANG Zhong-li ZHANG Meng-zheng LI Fu-yun |
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| Affiliation: | (xi＇ an Aerospace Propulsion Institute, Xi＇ an 710100, China) |
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| Abstract: | The temperature variation of gas-generator exhausting shell and turbine＇s inlet-outlet housing are analyzed during No, 001-003 hot test of liquid rocket engine （LRE）, With unsteady heat transfer methods, the temperature variation of turbine housing caused by the gas-generator working at different flow rate and efficient in the 003 time hot test were simulated. The simulation result shows that the overheating of turbine housing is because of too much high efficiency of gas-generator. |
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| Keywords: | liquid rocket engine turbine simulation calculation hot test |
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