Simulation Of Solid Rocket Motor Reaction Flowfield Based On EBU Model

In the design of solid rocket motor,the accurate calculation of internal flow field properties is very important to the performance prediction of internal ballistic parameter,efficient design and the manufacture of solid rocket motor.In the present,researches on simulation of solid rocket motor working process are 2-D simplified geometry models on the condition of fixed total temperature,without the consideration of the influence of the change of heat release in propellant combustion.But in the working process of real motor,the flow field is 3-D,and heat release in propellant combustion with the temperature,pressure,propellant burning rate in flow field are intercoupling and interacted.So the research of propellant burning and gas flow in the solid rocket motor is a very important part of numerical simulation of solid rocket motor working process,and of important significance to research on performance parameters and the design of solid rocket motor.A numerical simulation of solid rocket motor is made in this thesis with the software of FLUENT.There is three works in this thesis:one-step pure gas phase reaction,one-step reaction with particle that it doesn't take part in the reaction,and two-step reaction with particle.Then the influence among gas,particle and the reaction of particle will be discussed Finally,A accurate simulation of solid rocket motor can be regarded as a reference for experiment.Based on the basic theory of Weidong Cai and a 2-D model in the literature,a simulation under the microscale condition is made in this thesis and compared with the results in the literature to prove the correctness of the calculation method.According to the turbulent boundary layer theory of chemical reaction model,a simulation of the turbulent boundary layer on the surface of the solid propellant is made in this thesis.It analyzes the change law of flow field with combustion,two phase flow and transient,then compared with experimental results.A numerical simulation of solid rocket motor with a 2-D step type motor model is made with EBU model and k-? turbulent model in this thesis.Then the performance parameters in the solid rocket motor of one-step reaction with particle in different size,and find the law of these performance parameters can be shown with the simulation..The next work is that discuss the performance parameters of two-step reaction with particle,and find the law of performance parameters change.Last the final law among particle size,turbulent kinetic,energy dissipation rate and the chemical reaction rate will be shown.Based on the above research and analysis,we make a 3-D numerical simulation in the solid rocket motor with star grain and finocyl grain.Then the influence of the 3-D effect and the relation between propellant combustion and gas flow will be studied.The same time,the influence of particle participate in the reaction to the performance parameters will be discussed.Finally,the law among particle size,turbulent kinetic,energy dissipation rate and the chemical reaction rate can be shown.