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.
关键词
固体火箭超燃冲压发动机/气固两相流动燃烧/一次燃气/超声速流动/燃烧组织方案
Key words
solid rocket scramjet/gas-solid two phase flow combustion/primary gas/supersonic flow/combustion organization
维普
万方数据