摘要
为研究真空环境下液体的雾化特性及其影响因素,建立了真空环境喷雾实验系统。用水模拟液体推进剂,真空环境舱的初始真空度小于10Pa,采用高速动态分析系统测量了喷雾场。结果表明,真空环境下液体射流的闪蒸是其破碎与雾化的主要因素之一;喷射速度较低时喷口发生结冰现象;随着喷射雷诺数的增大,破碎长度变长而雾化锥角减小;喷射速度相同时,喷嘴直径增大,破碎长度和雾化锥角随之增大。
In order to study the atomization characteristic and its influence on liquid jet in vacuum, an experimental system was built, in which water was used instead of the liquid propellant, the initial vacuum degree in the vacuum cabin was lower than 10 Pa, and the high-speed dynamic analysis system was adopted to measure the atomization. The experimental results show that the flashing of the liquid jet in vacuum environment is one of the main factors for atomization of liquid jet, the icing phenomenon occurs on the edge of injector as the jet velocity is low, the length to break up increases and the spray angle decreases with the increase of the liquid Reynolds number in vacuum, and while the jet velocity is same, the larger the diameter of nozzle orifice is, the longer the length to break up will be and the more the spray angle will become.
出处
《火箭推进》
CAS
2010年第5期27-30,共4页
Journal of Rocket Propulsion
基金
总装备部预研项目
关键词
真空环境
空间火箭发动机
雾化特性
闪蒸
vacuum environment
space rocket engine
atomization characteristic
flashing
