摘要
为了研究气氧/气甲烷针栓发动机的燃烧特性,建立了气氧/气甲烷针栓发动机二维轴对称数值计算模型,湍流模型采用标准的k-ε双方程湍流模型,燃烧过程采用一步总包化学反应机理的涡耗散模型进行处理。数值仿真结果表明,针栓发动机在氧气和甲烷燃烧反应稳定时会产生较大的火焰锥角,温度场呈现带状分布,燃烧室内部流场存在两组回流区;随着喷孔位置远离针栓头部,燃烧效率增加,但火焰锥角不变;而环缝宽度增加,燃烧效率降低,火焰锥角增加;相反喷孔直径增加,燃烧效率增加,火焰锥角减小;在一定范围内燃烧效率随着火焰锥角增加而减小。
In order to study the combustion characteristics of the GOx/GCH4 pintle engine,a two-dimensional axisymmetric numerical calculation model of the engine was established.For the turbulence model,a standard k-εmodel was adopted and the eddy-dissipation model with one-step mechanism was applied to simulate the combustion process.The numerical simulation results show that when the combustion reaction between oxygen and methane was stable,a large flame angle was observed,the temperature showed a banded distribution,and two sets of recirculation zones existed inside the combustion chamber.The combustion efficiency increases with the position of orifice located away from the pintle tip,but the flame angle is unchanged.As the annular gap increasing,the combustion efficiency decreases,but the flame angle increases.To the contrary,the combustion efficiency increases while the diameter of the orifice increases,the flame angle decreases.Within limits,the combustion efficiency decreased with flame angle increasing.
作者
周康
李清廉
成鹏
常一冰
ZHOU Kang;LI Qinglian;CHENG Peng;CHANG Yibing(National University of Defense Technology, Changsha 410073, China)
出处
《火箭推进》
CAS
2018年第6期44-52,共9页
Journal of Rocket Propulsion
基金
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(NCET-13-0156)
关键词
针栓发动机
燃烧数值仿真
带状温度分布
喷孔位置
喷孔直径
环缝宽度
pintle engine
combustion simulation
a band distribution of temperature
pintle orifice position
pintle orifice diameter
annular gap
