| 液氧／甲烷气液喷注器试验研究 |
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| 引用本文： | 李丹琳,栾叶君,孙纪国.液氧／甲烷气液喷注器试验研究[J].火箭推进,2010,36(4):59-62. |
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| 作者姓名： | 李丹琳 栾叶君 孙纪国 |
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| 作者单位： | 北京航天动力研究所,北京,100076 |
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| 摘 要： | 介绍了液氧／甲烷气液喷注器热试验情况，试验燃烧室压力7．1～7．4MPa，混合比3．5～3．9。研究了不同的喷嘴结构参数对燃烧性能和流量特性的影响。获得了燃烧效率、流量系数、振动、点火性能以及积炭特性等重要参数。
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| 关 键 词： | 液氧／甲烷 推力室 燃烧效率 同轴式喷嘴 试验 |
Experimental investigation on LOX/CH4 subscale thrust chamber |
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| Li Danlin,Luan Yejun,Sun Jiguo.Experimental investigation on LOX/CH4 subscale thrust chamber[J].Journal of Rocket Propulsion,2010,36(4):59-62. |
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| Authors: | Li Danlin Luan Yejun Sun Jiguo |
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| Institution: | (Beijing Aerospace Propulsion Institute, Beijing 100076, China) |
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| Abstract: | The firing tests of a LOX/CH4 subscale thrust chamber are presented in this paper. The chamber pressure of the tests is between 7.1 and 7.4MPa. The mixture ratio is between 3.5 and 3.9. Effects of design parameters on the LOX/CH4 coaxial injector combustion and discharge performance are investigated by firing tests. Some key parameters are obtained such as combustion efficiency, discharge coefficient, vibration, ignition and the soot formation characteristics. The firing tests are important base for the development of a LOX/CH4 rocket engine. |
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| Keywords: | LOX/CH4 subscale thrust chamber C＊efficiency coaxial injector hot fire test |
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