液氧/甲烷火箭发动机燃烧稳定性影响规律分析  

Numerical Study of the Effect of LOX/CH4Rocket Engine Combustion Stability

作　　者：孙阳 丰松江 聂万胜 

机构地区：[1]装备学院研究生院,北京101416 [2]装备学院航天装备系,北京101416

出　　处：《导弹与航天运载技术》2012年第5期39-42,共4页Missiles and Space Vehicles

基　　金：国家自然科学基金资助项目(51076168)

摘　　要：预防和控制燃烧不稳定性是液氧/甲烷火箭发动机研制过程中的一项重要工作。对液氧/甲烷火箭发动机的燃烧过程进行单相、两相流场数值仿真,分析得到混合比、甲烷喷前温度、液氧雾化直径对发动机燃烧稳定性的影响规律。结果表明:燃烧室内易出现中频燃烧不稳定性;混合比的影响较为明显,对于某一工况,存在易发生不稳定燃烧的混合比区间;甲烷喷前温度的影响较小;液氧雾化直径较小易导致燃烧不稳定,燃烧室喷注器设计时需折中考虑雾化质量与燃烧效率等方面的因素。The prevention and control of the combustion instability is an important issue in the process of developing the LOX/CH4 rocket engine. The combustion process of the LOX/CH4 rocket engine is studied by using single-phase and two-phase numerical simulation, and the effect of oxidant-fuel ratio, methane injection temperature and liquid oxygen atomization diameter on the combustion stability are analyzed. The results show that the combustion chamber is easy to appear intermediate frequency combustion instability, the influence of the oxidant-fuel ratio is obvious, and for a given condition, there is a mixing ratio range that easy occurs the unstable combustion; the influence of the methane injection temperature is small; and smaller liquid oxygen atomization diameter is easy to cause the combustion instability. The quality of atomization and combustion efficiency need to be considered simultaneously in the design of combustion chamber injector.

关 键 词：液体火箭发动机 不稳定燃烧 数值计算 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]