Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector
Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector
复制标题
同轴喷射器液氧/液甲烷蓄热式冷却燃烧室综合设计方法
DOI：
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发表时间：
2009
期刊：
影响因子：
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通讯作者：
N. Yatsuyanagi
中科院分区：
文献类型：
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作者：
N. Yatsuyanagi
介绍了同轴式液氧/液态甲烷火箭发动机燃烧室的综合设计方法，并对真空、3.43MPa、推力100 kN的再生冷却燃烧室进行了初步设计。获得了满足目标C* 效率大于98%和燃烧稳定性的燃烧室的合理尺寸。
A comprehensive design method for a LOX/Liquid-Methane (L-CH4) rocket engine combustor with a coaxial injector and the preliminary design of the regenerative cooling combustor with 100-kN thrust in vacuum at a combustion pressure of a 3.43 MPa are presented. Reasonable dimensions for the combustor that satisfy the targeted C* efficiency of more than 98% and combustion stability are obtained.