초록 열기/닫기 버튼
Three-dimensional heat transfer numerical analysis of the regenerative cooling system applied to the combustion chamber of the scramjet propulsion system in the environment of mach number 4 to 6 was conducted. The number of cooling channels and the mass flow rate of fuel per unit channel were determined by the size of the combustion chamber and the air mass flow rate and the equivalent ratio to which the scram mode and the ram mode were assumed. The aspect ratio of the cooling channel was divided into four cases(1,2,4 and 8) and the assumed heat flux condition on the combustor was 1.5MW/m2 to 2.5MW/m2. Among the ten turbulent heat transfer duct flow models, the Bae-Kim model suits the best to the supercritical n-dodecane cooling channel and the heat transfer model was improved by revising the geometry effect and one-sided heat effect.
