| 液氧甲烷单喷嘴燃烧性能数值仿真研究 |
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| 引用本文： | 刘红珍,田原,孙纪国.液氧甲烷单喷嘴燃烧性能数值仿真研究[J].火箭推进,2014(1):56-59,91. |
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| 作者姓名： | 刘红珍 田原 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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| 基金项目： | 国家863项目（2006AA702067） |
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| 摘 要： | 为了研究液氧甲烷同轴剪切式喷注器结构参数变化对燃烧性能的影响,以单喷嘴为物理模型进行了燃烧数值仿真.研究表明：适当增加氧喷嘴出口壁厚和增加喷嘴个数均能提高喷注器燃烧效率,其中增加喷嘴个数对燃烧效率的影响更为显著.
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| 关 键 词： | 液氧甲烷喷注器 单喷嘴 燃烧性能 数值模拟 |
Numerical simulation of combustion performance of LOX/methane single nozzle |
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| LIU Hong-zhen,TIAN Yuan,SUN Ji-guo.Numerical simulation of combustion performance of LOX/methane single nozzle[J].Journal of Rocket Propulsion,2014(1):56-59,91. |
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| Authors: | LIU Hong-zhen TIAN Yuan SUN Ji-guo |
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| Institution: | (Beijing Aerospace Propulsion Institute, Beijing 100076, China) |
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| Abstract: | In order to study the influence of structure parameter change of co-axial shear LOX/methane injector on its combustion performance, a single nozzle is taken as a physical model to carry out the combustion numerical simulation. The research shows that the appropriate increase of the wall thickness at outlet of LOX nozzle and addition of the nozzle quantity can improve the com- bustion efficiency of the injector, and the effect of addition of the nozzle quantity on the combustion efficiency is greater. |
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| Keywords: | liquid oxygen/methane injector single nozzle combustion performance numerical simulation |
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