文中利用数值模拟研究了不同来流条件下固体火箭超燃冲压发动机的燃烧特性。采用基于密度的二阶迎风格式对发动机内流场进行模拟,湍流模型与燃烧模型分别采用SSTk-ω模型与涡团耗散模型。结果表明,随来流马赫数的增大,火焰温度与最大化学反应速率均增大;燃烧效率随来流马赫数的增大而减小,且燃烧效率低于50%;燃烧效率的减小导致补燃室的推力与比冲下降。随来流马赫数的变化,应适当调节富燃燃气流量,以保证发动机的燃烧性能。

In this paper, the combustion characteristics of solid rocket scramjet under different inflow conditions were studied by numerical simulation. The internal flow field of engine was simulated by using the two order upwind format based on density, and the turbulence model and combustion model adopted SST k-ω model and eddy dissipation model respectively. The results indicated that the flame temperature and the maximum chemical reaction rate both increased with the increase of inflow Mach number. The combustion efficiency decreased with the increase of inflow Mach number, and the combustion efficiency was lower than 50%. The decrease of combustion efficiency led to the decrease of thrust and specific impulse of secondary combustion chamber. With the change of inflow Mach number, the fuel rich gas consumption should be adjust appropriately to ensure the combustion performance of engine.