摘要
为了研究大流量低混合比氢氧喷嘴的燃烧特性,进行了燃气发生器变工况热试验。试验结果表明,不同工况下,氢氧喷嘴的燃烧效率均高于0.986,燃气发生器出口截面温度差值小于±30K;相对于工况A,工况B的点火延迟时间更长;对于特定的喷嘴结构和燃烧室容积,超临界氢/液氧同轴直流式喷嘴存在一个稳定工作的氧喷嘴压降下限,如果工作环境低于该下限,易激发燃烧不稳定。
In order to investigate the combustion performance of large flow rate and low mixture ratio Hydrogen/Oxygen shear coaxial injector,the gas generator fire tests are carried out with two conditions.The experiment results show that the combustion efficiency of Hydrogen/Oxygen injector is higher than 0.986 and the temperature uniformity of gas generator outlet is lower than±30 K with different conditions.Compared with condition A,the ignition delay time is longer with condition B.For a specific Hydrogen/Oxygen shear coaxial injector and combustor volume,a stability boundary may be established by varying the LOX injection pressure drop.
作者
潘刚
牛旭东
丁兆波
孙纪国
Pan Gang;Niu Xu-dong;Ding Zhao-bo;Sun Ji-guo(Beijing Aerospace Propulsion Institute,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2020年第5期43-47,共5页
Missiles and Space Vehicles
关键词
大流量
低混合比
氢氧喷嘴
变工况
燃烧特性
large flow rate
low mixture ratio
Hydrogen/Oxygen injector
variable-flow
combustion performance
