摘要
在带有液膜冷却双组元推力器的设计过程中,对燃烧室的数值仿真是一项非常重要的工作.充分考虑了常被忽略或简化处理的推进剂雾化、液滴破碎、液膜形成等重要过程,选取EDC燃烧模型和realizable k-ε湍流模型,采用有限体积计算方法得到燃烧室内部液滴分布、液膜分布、静温分布等重要数据.最后,根据所得结果阐述了燃烧室内的详细工作过程,并着重分析了液膜的分布特点以及对壁面的冷却作用,得到了两个与液膜冷却相关的结论.
In the design of film-cooled bipropellant thruster, the numerical simulation of the combustion chamber is a necessary step. In this paper, process of atomizing of the liquid propellant, breaking up of droplets, liquid film formation are taken into account, and the EDC combustion model and the realizable k-ε turbulent flow model are selected. Distributions of droplets, liquid film and static temperature are obtained by using the numerical simulation. At last, based on the analysis of simulation results, the working process in combustion chamber are interpreted, and two conclusions on the liquid film cooling are derived.
出处
《空间控制技术与应用》
2012年第2期58-62,共5页
Aerospace Control and Application
关键词
双组元
液膜冷却
燃烧室
数值模拟
bipropellant
liquid film cooling
combustion chamber
numerical simulation
