| 振荡环境下推进剂液滴亚临界蒸发响应特性 |
| |
| 引用本文： | 刘卫东,周进,王振国.振荡环境下推进剂液滴亚临界蒸发响应特性[J].航空动力学报,2001,16(1):52-54. |
| |
| 作者姓名： | 刘卫东 周进 王振国 |
| |
| 作者单位： | 国防科技大学 航天技术系, |
| |
| 基金项目： | 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。
|
| 关 键 词： | 液体火箭发动机 推进剂 液滴蒸发 不稳定燃烧 |
| 文章编号： | 1000-8055(2001)01-0052-03 |
| 收稿时间： | 1999/7/20 0:00:00 |
| 修稿时间： | 1999年7月20日 |
Response of Propellant Droplet Subcritical Evaporation to Environmental Pressure Oscillation |
| |
| LIU Wei-dong,ZHOU Jin and WANG Zhen-guo.Response of Propellant Droplet Subcritical Evaporation to Environmental Pressure Oscillation[J].Journal of Aerospace Power,2001,16(1):52-54. |
| |
| Authors: | LIU Wei-dong ZHOU Jin and WANG Zhen-guo |
| |
| Institution: | 1st Dept., National University of Defense Technology, Changsha410073, China;1st Dept., National University of Defense Technology, Changsha410073, China;1st Dept., National University of Defense Technology, Changsha410073, China |
| |
| Abstract: | 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. |
| |
| Keywords: | liquid rocket engines propellants droplet evaporation combustion instability |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
| 点击此处可从《航空动力学报》下载免费的PDF全文 |
|
