Study On The Flow And Heat Transfer Characteristics Of Liquid Propellant In Porous Media

In the field of liquid rocket engine research,the scientific community has made significant progress in rocket engines,rocket structural design,propulsion technology,and high-efficiency energy.However,with the development of integrated technologies in the aerospace field,high thrust and reusable carriers require that the corresponding thermal protection technology must have two basic characteristics of extremely high cooling capacity and protection of thermal protection structures.Porous media has a strong structural protection and cooling heat transfer capabilities,and has applications in many areas.In this paper,based on the regenerative cooling system of liquid rocket engine,the application of enhanced heat transfer in porous media,especially the new type of liquid propellant rocket propellant,is carried out in-depth study of heat transfer enhancement in the pipe.In this paper,the porous media as the research object,in order to better obtain the porous media cooling effect in the rocket engine cooling channel,the use of steady-state numerical analysis of the different types of propellants in the presence of porous medium heat transfer effect The effect of flow heat transfer of liquid coolants such as n-decane and nitrous oxide was studied.At the same time,the physical properties of the porous media itself,the effect of the flow and heat transfer conditions in the pipe on the heat transfer effect,and the filling structure of the porous media in the pipe itself have been studied.The porous media filled structures studied here are mainly semi-filled.Combined with the comprehensive comparison of the flow resistance of the heat transfer coefficient,the results related to the fluid properties and the properties of the porous media were obtained.In the non-steady state calculation,through the unsteady calculation of water and NOFB29 cooling media,we obtained the results of a certain flow heat transfer with different boundary heat fluxes and porosity.Among them,NOFB29 is a new rocket propellant.The numerical calculation of the mixed fluids enhances the heat transfer and application of the porous medium in the cooling channel and helps with it.The results of changes in the internal structure of the porous media and the temperature of the fluid over time were obtained.Finally,a high-low temperature test bench was used for heat exchange experiments.Through repeated experiments on water and aviation kerosene,the actual heat transfer effect of the porous medium was visually reflected.The actual heat transfer test of the porous medium was conducted,and different cooling working fluids were compared.The actual channel heat transfer effect under different flow rates.The flow and heat transfer characteristics of porous media under high and low temperature conditions were calculated experimentally,which provided a feasible solution for the study of porous media.In this paper,through the combination of numerical simulation and experimentation,the results of studies on the properties of different cooling media and material structures suggest that the porous media in the liquid rocket cooling channels have actual enhanced heat transfer characteristics,but a certain degree of flow resistance.It will affect the overall economy,and it still needs further exploration in the cooling of porous media in the aerospace field.