燃气侧喷固冲发动机补燃室流场三维数值研究

3D Numerical Simulation of Flow Field in Secondary Combustion Chamber of Fuel Gas Dual-Injection Ramjet Engine

采用标准k-ε二方程模型和涡团耗散模型对固体火箭冲压发动机补燃室内流场进行了三维数值模拟研究。考虑燃气喷射角度,补燃室出口反压对燃烧流场的影响。得出了反应物和产物组分、温度等发动机参数的变化趋势。其中燃气喷射角度分别为30°,45°,60°。结果表明:增加喷射角度,补燃室头部温度升高,燃料完全燃烧所需补燃室长度减少;增大出口反压有利于补燃室内燃烧的进行。该结论对固冲发动机补燃室的理论设计和实验优化有重要作用。

This paper presents the 3 D numerical simulation of flow field in secondary combustion chamber of rocket ramjet engine by using the standard k - εtwo equation turbulent model and ED model. The effects of the secondary combustion chamber exit-pressure and fuel gas injecting angle on the combustion flow field are considered. The variation trend of reactant and resultant species, temperature and so on is obtained. The fuel gas injecting angle is 30°, 45°, 60° respectively. The results indicate that, when increasing the injecting angle, the head temperature of secondary combustion chamber will be higher, and the length of secondary combustion needing to be completely combusted can be shortened. When increasing the exit - pressure of the secondary combustion chamber, the combustion efficiency can be improved. The conclusion is important for the design and optimization of afterburning of fuel gas dual- injection ramiet engine.