Study On Gas-Particle Mixing Characteristics Of Solid Rocket Scramjet Combustion Chamber

The gas-solid two-phase flow between the injector of the solid rocket supercombustion ramjet engine and the combustion chamber is a relatively complicated supersonic two-phase flow process,which involves the interaction between particles and gas and convective heat transfer and the collision of particles and walls.Process etc.This topic intends to conduct a three-dimensional numerical calculation and analysis of the supersonic gas-solid two-phase flow in the engine injector and the combustion chamber through an appropriate numerical model,summarize the basic flow laws,and on this basis,optimize the structure and explore combustion Indoor gas-solid two-phase flow combustion process.First,based on experiments,a basic model of gas-solid two-phase supersonic flow and injection is established based on the SST k-w turbulence model and the DPM discrete phase random walk model.Vortex dissipation/finite rate model and particle phase multisurface reaction model are used to describe the combustion process of gas phase and particles,respectively.Next,the gas-solid two-phase flow in the injector was analyzed,and the effects of particle phase mass fraction,particle size and outlet back pressure on the gas-solid twophase flow blending were explored.The research shows that in the injector with nozzle configuration,the gas-solid two-phase flow and the pure gas phase flow are quite different.The effects of the particle phase,including changes in diameter and mass fraction,will have a greater impact on the mass flow distribution of the gas-solid two-phase gas at the outlet of the injector.This will have a greater impact on the subsequent gas split.If the design is not reasonable,it is easy to have uneven fuel flow distribution,which will affect the efficiency of injection blending.In addition,the gas-solid two-phase flow in the injector is more sensitive to the back pressure of the outlet.Under working conditions,the back pressure is easily too large,which makes the injector not working properly.This also needs careful consideration in subsequent injector design.In this chapter,the gas-solid two-phase sonic jet mixing process under the condition of supersonic flow is studied in depth.The interaction of the particulate phase with the gas-phase gas and air during the injection process was explored.The results of the study show that the addition of the particulate phase does not significantly change the overall flow field structure of the gas phase,but has a certain effect on the local flow.The nature of the interaction between the particle phase and the gas phase did not change throughout the jet blending process.The motion process of the particle phase is the result of the combined action of the drag force and its own inertia.The gas-phase turbulence structure has little effect on it.In addition,the basic mixing law of gas-solid two phases is analyzed and summarized..Finally,the gas-solid two-phase combustion process in the solid rocket scramjet was studied.At present,the calculation results of numerical simulation have a larger error than the experimental results.The main reason is that the description of the motion and combustion of the particle phase is not accurate enough.In the follow-up research process,it is necessary to consider the influencing factors such as the particle size and the complex chemical reaction kinetic mechanism of the particle phase under high temperature and high speed.