国防科技大学学报2016，Vol.38Issue(2)：12-18,7.DOI:10.11887/j.cn.201602003
流量连续可调火箭发动机极度富燃燃烧特性
Combustion characteristics of an extreme fuel-rich throttleable rocket engine
摘要
Abstract
To study the combustion characteristics of a rocket engine under continuous throttling,a continuous throttling experiment was conducted by using GOX (gaseous oxygen )/kerosene as propellants.Mass flow rate of kerosene was continuously throttled by a throttleable cavitation Venturi nozzle.Successful ignition under fuel rich condition (mixture ratio ranged from 0.405 to 0.690)and the continuous throttling of mixture ratio and combustion gas flow rate were achieved.Results show that chamber pressure increases with the decrease of kerosene flow when the mixture ratio is less than 0.535 but decreases when the mixture ratio is greater than 0.535.Meanwhile,characteristic velocity and combustion efficiency increase with the increasing mixture ratio,but the increasing ratio is bigger when the mixture ratio is less than 0.535 than that when the mixture ratio is greater than 0.535.The results indicate that the mass flow rate of propellants and combustion efficiency simultaneously affect the chamber pressure.Combustion efficiency dominates the chamber pressure when the mixture ratio is less than 0.535 while mass flow rate of propellants dominates when the mixture ratio is greater than 0.535.关键词
火箭基组合循环/火箭发动机/气氧/煤油/连续调节Key words
rocket based combined cycle/rocket engine/GOX/kerosene/continuous throttling分类
航空航天引用本文复制引用
成鹏,李清廉,张新桥,康忠涛..流量连续可调火箭发动机极度富燃燃烧特性[J].国防科技大学学报,2016,38(2):12-18,7.基金项目
国家自然科学基金资助项目（11472303，11402298）；新世纪优秀人才支持计划资助项目 （）
