燃烧室结构对固液火箭发动机燃烧与流动的影响研究

建立了85%H2O2-PE固液火箭发动机氧化剂H2O2催化分解、PE燃料热解以及热解气体与氧化剂分解气体扩散燃烧的综合模型,计算了固液火箭发动机燃烧室轴对称二维内流场,对不同结构燃烧室内流场的计算结果进行了对比,研究了补燃室和氧化剂入口突扩结构对发动机燃烧性能的影响.结果表明,增加氧化剂入口突扩段有利于发动机稳定工作和充分燃烧,增加补燃室长度可以提高发动机平均燃烧温度,使燃烧更加充分.

Effects of combustion chamber structure on combustion and flow of hybrid rocket motor

The synthesis model of H2O2 oxidizer decomposition, PE fuel pyrogenation and diffusion combustion of its decomposition gas and pyrogenation gas of 85% H2O2-PE hybrid rocket motors was derived. The 2D axisymmetric internal flow fields in combustion chamber of hybrid rocket motors were calculated. The calculation results of combustion chambers with different structure were compared, and the effects of afterburning chamber structure and oxidizer inlet expansion structure on burning properties of hybrid rocket motors were investigated. The results show that the increment of oxidizer inlet expansion is favorable for efficiency and stabilization of the motor,and the increase of length of the afterburning chamber can raise the average burning temperature and improve the combustion efficiency.