振荡环境下推进剂液滴亚临界蒸发响应特性  

Response of Propellant Droplet Subcritical Evaporation to Environmental Pressure Oscillation

作　　者：刘卫东[1] 周进[1] 王振国[1] 

机构地区：[1]国防科技大学航天技术系,湖南长沙410073

出　　处：《航空动力学报》2001年第1期52-54,共3页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目! (19882 0 0 8)

摘　　要：针对推进剂液滴在惰性气体中的蒸发过程建立了非定常物理模型 ,并应用全隐差分格式离散模型方程进行数值求解。研究了液滴蒸发过程对环境气体压力振荡的响应特性 ,可为液体火箭发动机不稳定燃烧分析提供理论基础。A non-steady model of propellant droplet evaporation in inert gas has been developed.The model equations have been solved by numerical method with full implicit central scheme.The results show that,when the droplet diameter keeps unchanging,there exists a special pressure frequency,to which the droplet evaporation responds most strongly.In this case the droplet evaporation oscillation approaches to its maximum as the droplet temperature comes near the equilibrium temperature.Therefore,it is reasonable to believe that propellant evaporation could trigger unstable combustion in the rocket engine.

关 键 词：亚临界蒸发 液体推进剂火箭发动机 惰性气体 液滴蒸发 不稳定燃烧分析 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]