摘要
文中提出了具有液相离解反应的推进剂液滴高压蒸发模型,同时还考虑了燃气中极性气体成份对液滴蒸发的影响,并以N_2O_4推进剂液滴为例分析了具有液相离解反应的推进剂蒸发规律。结果表明,此类推进剂高压蒸发并不服从非液相离解反应推进剂的t_b～(?)。规律。模型的提出为液体火箭发动机燃烧室燃烧过程分析提供了新的液滴蒸发理论数据和计算方法。
In this paper the model of the propellant droplet evaporation with liquid phase dissociation reaction at high ambient pressure is developed, and theeffect of polar gase compositions in combustion gases on the propellant dropletevaporation is taken into account. The characteristics of propellant droplet eva-poration of the liquid phase dissociation reaction are analyzed by an exampleof the N_2O_4 liquid droplet evaporation. The calculation results show thatthis kind of propellant at high pressure evaporation does not obey the law ofnon-liquid phase dissociation reaction propellant. This model provides the newtheoretical data and the calculation metheod for the analysis of the combustionprocess of the liquid rocket engine combustor.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
1989年第1期59-65,共7页
Journal of National University of Defense Technology
关键词
推进剂
离解反应
高压蒸发
dissociation
high pressure
evaporation
propellant
