Numerical Simulation And Experimental Analysis Of Adiabatic Wall Ablation In Solid Rocket Ramjet

In the working process of the solid rocket ramjet,the secondary combustion gas afterburning interior existence,the head of air jet and the combustion gas jet interaction permeability mixed involves multiple recirculation region and the boundary layer of mutual coupling problem,due to the increase of heat transfer and thermal protection layer of shell's thinning became more prominent.In order to carry on the reasonable computing research on these issues,in this paper,the complementary combustion interior of fluid-solid heat coupling problem of numerical analysis,supplemented by relevant experiments.(1)In solid rocket ramjet test platform of the choking lateral inlet ramjet,thermal protection layer of afterburning chamber ablation experiments,the experimental results show that the lateral inlet of solid rocket ramjet,inlet downstream the leeward surface temperature is high,the thermal chemical ablation is extremely serious.(2)In view of the interior flow field of solid rocket ramjet complementary combustion in complex problems such as turbulent flow and composition of chemical reaction,combined with multicomponent chemical reaction Compressible gas equation and particle trajectory model,the finite volume method,computational scheme,turbulence model,the gas phase turbulent combustion using eddy dissipation model,two phase turbulent combustion using simplified PDF model,established the three-dimensional multicomponent gas solid two phase flow field simulation method,the related numerical calculation program,to fill in the process of secondary combustion chamber flow thermal coupling two phase flow problems in numerical calculation.The simulation results show that near the inlet temperature is higher because a large number of aluminum particles and a combustion within the components in the downstream of the inlet and the mainstream of intense reaction,oxygen in the condensed phase under the influence of the main inlet particles dispersed around the inlet jet,and collision with the wall,the wall thermal chemical ablation serious cases,in addition,its fuel ratio rises,the inlet high temperature around the combustion chamber head forward,the results of numerical simulation and experiment results have better fitting and made good for wall ablation of numerical simulation(3)For complementary combustion flow field in the interior wall and between different ways of heat transfer,thermal physical model of calculating model and add the source term to calculate the mass flow rate on carbon method calculates thermal protection layer near wall ablation rate,can be described is established oxygen-rich environment fill ramjet combustion chamber flow field and structure field coupling structure characteristic model,the related calculation program to calculate.Calculation results show that indoor temperature in the inlet of the downstream complementary combustion and thermal chemical ablation with the increase of engine working longer and,at the same time step inside temperature and decreasing trend along the axial direction.