Study On Coupled Heat Transfer In Scramjet Combustor And Its Cooling Structuer

High-temperature environment in scramjet combustor requires adopting active cooling structure. Understanding and analyzing of high-temperature thermal environment in scramjet combustor and the coupled heat transferring characteristic with cooling structure is a precondition for the design of the active cooling thermal protection structures in the scramjet combustor. It is significant for the development of supersonic flight. Through numerical simulation and theoretical analysis, complex thermal environment in scramjet combustor and coupled heat transfer character with cooling structure were investigated in this thesis.Firstly, by analyzing the supersonic combustion in the scramjet combustor, the heat transfer coupled air-actuated convection and radiation, the convective heat transfer mechanics of the active cooling channel, the coupled heat transfer model was constructed. On above basis, the distributing of heat flux in combustor and heat transfer character of cooling channel were numerically simulated and investigated by the Fluent software.The non-premixed combustion model was adopted to predict the thermal environment of scramjet combustor. The effect of radiation heat transfer in the course of supersonic combustion was analyzed. Under different heat boundary such as adiathermal wall, isothermal wall and nonhomogeneous wall, the heat flux distributing characteristics of wall in combustor were compared.Base on the cognition of the thermal environment in combustor and it's influence factors, the design scheme of the active cooling structure was presented primarily. From simulating the convective heat transfer capability of cooling channel in laminar and turbulent flow pattern, the feasibility of this design scheme was verified.From the study in this thesis, a valuable reference for the further investigation of coupled heat transfer in the scramjet combustor and the development of the active cooling technology were provided.