论文部分内容阅读
为提高固体火箭冲压发动机二次燃烧效率,将旋转射流技术引入固体火箭冲压发动机设计,采用Re-alizable k-ε湍流模型、单步涡团耗散燃烧模型以及KING硼粒子点火和燃烧模型,利用Fluent软件开展了旋转进气和一次燃气旋转含硼固体火箭冲压发动机补燃室三维反应流场流数值分析。研究结果表明,当空气射流切向进入补燃室时,气流产生的旋转均使燃料与空气的混合更充分,燃烧效率更高。当气流切入角度增大时,补燃效率先升后降,对于具体发动机结构,存在一个使燃烧效率最大的切入角,针对研究的模型发动机结构,此值在20°附近;当一次燃气旋流数的增加,二次燃烧效率呈逐渐增高的趋势。
In order to improve the secondary combustion efficiency of solid rocket ramjet, rotary jet technology is introduced into the design of solid rocket ramjet engine. Re-alizable k-ε turbulence model, single-step vortex dissipative combustion model and KING boron particle ignition and combustion model are adopted. Fluent software carried out a three-dimensional numerical analysis of the flow field in the afterburner of a rotary gas inlet and a gas-fired boron-containing solid rocket ramjet engine. The results show that when the air jet tangentially enters the afterburning chamber, the rotation of the air flow makes the mixture of fuel and air more fully and the combustion efficiency is higher. When the cutting angle of airflow increases, the charge-back efficiency first increases and then decreases. For a specific engine structure, there is a cutting angle that maximizes the combustion efficiency. For the model engine structure studied, this value is around 20 °. When a gas swirling The increase of number, the secondary combustion efficiency showed a gradual increase in the trend.