摘要
为了研究双组元推力器喷注角度对液膜分布的影响,基于气液两相模型建立某型双组元(MMH/NTO)推力器燃烧室内雾化、液膜、流动的数学模型,忽略了燃烧过程,同时假设喷注推进剂全部为NTO,采用有限体积的数值方法计算了不同喷注角度下燃烧室壁面液膜的分布情况.通过分析计算结果得出随着喷注角度的增加,液膜区域向喷注壁面靠近;不同喷注角度下的液膜长度均为30mm左右,喷注半角为45°～55°时,液膜平均厚度变化明显.
To analyze how the bipropellant thruster injection angles influence the liquid-film distribution,we propose a numerical method to calculate the distribution of the liguid-film on the inwall of combustion chamber with different injection angles by using the finite volume method.The proposed approach is based on the gas-liquid biphase model under the assumptions there is no combustion in the combustion in the combustion chamber,and the propellant is all NTO.The calculation results show that the liquid-film moves to the direction of injector as injection angle increase.The lengths of liquid-film are all around 30mm under different injection angle.However,the liquid-film thickness changes a lot when half injection angle is between 45°and 55°.
出处
《空间控制技术与应用》
2012年第6期45-49,共5页
Aerospace Control and Application
基金
十二五总装备部预研课题资助项目(0000080700800001002020017)
关键词
双组元
液膜分布
喷注角度
bipropellant
liquid film distribution
injection angle
