Numerical research on gas injection combustion of solid rocket scramjet
Considering some problems in the combustion chamber of solid rocket ramjet,such as short fuel residence time,difficult mixing with air flow,poor flame stability,and low particle combustion efficiency,based on the Eulerian Lagrange method,a two-phase flow combustion simulation model was established and the primary gas was simplified by using the minimum free energy method and the law of conservation of energy and mass.Based on a solid rocket scramjet model with a cavity flame stabilizer,the influences of different gas injection angles and positions on temperature rise efficiency,total pressure recovery coefficient,cavity performance and particle combustion efficiency were explored.The results showed high calculation accuracy of this method.It was found that increasing the gas injection angle could improve the fuel penetration depth and increase the particle combustion efficiency,but the total pressure loss would increase;the change of gas injection location affected the combustion efficiency of particles not only because of the particle retention time,but also because of the temperature distribution in the region with the particles.
solid rocket scramjetgas-solid two phase flow combustionprimary gassupersonic flowcombustion organization
万方数据
维普
