摘要
为获得固液发动机固体燃料燃面退移的控制因素和机理,开展了数值仿真和试验研究。建立二维轴对称计算模型,考虑燃料与氧化剂的混合燃烧和流动过程,计算得到了固液发动机工作过程中的温度、压强、速度和组分的分布,以及不同时刻固体燃料的燃面形貌。仿真与试验结果的对比证明了计算方法的有效性。结果表明:固液发动机的燃面呈现显著的非平行退移特征;燃烧室压强对燃面退移不均匀性的影响可忽略;控制燃面退移的主要因素是燃气传向固体燃料表面的热流密度,燃料表面的温度变化是宏观表现。在靠近喷嘴位置,燃面退移的热量传递主要受燃烧反应过程控制,而靠近喷管处燃面退移的热量传递主要受燃气流动过程控制。研究为固液发动机的装药优化设计和高效燃烧组织提供了理论依据。
To understand the domination factors of solid-fuel regression in a hybrid rocket motor, numerical simulation and experimental study were carried out in this paper. A 2D axisymmetric model was derived and the mixed combustion with flow of fuel and oxidizer was considered. The distributions of temperature, pressure, velocity and component of combustion products, as well as burning surface while hybrid rocket was working were acquired from simulation. There is a good agreement between simulation and experiment results, and the validity of numerical method is demonstrated. The results showed that the burning surface was not parallel. The effects of chamber pressure on the nonuniformity of solid fuel regression could be ignored. The domination factor which controlled the regression was heat flux to the surface of solid fuel, and the temperature variation of solid fuel surface represented that of heat flux. The heat transition of solid-fuel regression near the injector was controlled by chemical reaction process. However, it was dominated by flow and convection of combustion products near the inlet of nozzle. The knowledge of domination factors provides theory evidence for optimization of grain design and combustion organization.
出处
《上海航天》
CSCD
2017年第1期62-66,共5页
Aerospace Shanghai
基金
国家863计划资助(2014AA7023027)
关键词
固液发动机
燃面退移
控制因素
燃料热解
非平行退移
热流密度
燃烧反应过程
燃气流动过程
hybrid rocket
regression
domination factors
fuel pyrolysis
norrparallel burning surface
heat flux
chemical reaction process
flow and convection of combustion products
