Numerical Simulation And Experimental Study On Mixed Combustion Of Solid Rocket Scramje

How to effectively organize the mixed combustion of rich combustion gas in solid rocket scramjet combustion chamber,especially the mixed combustion of particle phase,so as to improve the performance of the combustion chamber has always been a big problem that baffles and hinders the engineering development and application of solid rocket scramjet.In this paper,the basic structure of the combustion flow field of the high speed solid ramjet with rich gas transverse jet is constructed.By selecting and establishing a reasonable numerical method,the three-dimensional gas-solid two-phase flow combustion simulation is carried out on the combustion chamber based on this structure,and the basic influence law of the air-fuel ratio and other factors on the gas-solid two-phase mixed combustion performance in the combustion chamber is obtained.It provides the basis for the design of the working condition of the ground direct connection test.The influence of these factors on the performance of the combustor is further studied and the numerical calculation method is verified by conducting ground direct connection tests.Finally,the ignition and flame propagation process of rich combustion gas in the combustion chamber were observed and analyzed by high speed camera.It provides a reference for further research on improving the combustion efficiency of boron-containing oxygen-poor fuel in solid rocket scramjet and regulating the heat release distribution in combustion chamber.In this paper,the gas-solid two-phase mixing combustion in the combustion chamber is simulated by numerical method,and the influence of parameters such as air-fuel ratio,location of turbulence structure and incoming flow conditions on the gas-solid two-phase flow mixing in the combustion chamber is investigated.The results show that changing the air-fuel ratio can affect the combustion performance of the gas by changing the injection depth of the gas jet.When the incoming flow condition and the combustion chamber configuration are constant,there is an optimal air-fuel ratio to make the combustion performance of the combustion chamber best.The vortex structure can be formed to improve the mixed combustion performance of the nearby gas.When the coupling degree between the position of the turbulence structure and the backward step is good,the mixed combustion performance of the whole combustion chamber can be improved.The inflow condition will affect the size and shape of the reflux area of the backward step,thus changing the influence of the reflux area on the gas jet.When the reflux area is too small to be well coupled with the gas jet,the combustion performance in the combustion chamber will be reduced.The ground direct connection test platform of solid rocket scramjet engine was built,and the effects of air-fuel ratio,the location of turbulence structure and incoming flow conditions on combustion chamber performance and boron particle combustion performance were further analyzed by means of tests.The experimental results are in good agreement with those obtained by numerical simulation.By opening a window on the side wall of the combustion chamber and using the method of high speed photography with filter plate,the high speed photography of the rich gas injection area after ignition in the test was obtained and analyzed,including the flame morphology,particle phase distribution and distribution.The ignition and flame propagation process of rich combustion gas in the combustion chamber are obtained and the results of numerical simulation and experiment are verified by visual phenomena.