• cooling channel
• cooling system
• heat transfer coefficient
• lpr
• nusselt
• thermal stratification

The thermal phenomena in rocket engines involve interactions among a number of processes, including, combustion in the thrust chamber, expansion of hot-gases through the nozzle, heat transfer from hot gases to the nozzle wall via convection and radiation, conduction in the wall, and convection to the cooling channel. The complexity of the thermal analysis in rocket engines is due to three-dimensional geometry, coolant and hot gas heat transfer coefficient dependence on the pressure and wall temperature, unknown coolant pressure drop and properties, axial conduction of heat within the wall, and radiative heat transfer between gases and surfaces of the engine.

The thesis project carried out at TUM of Munich (Germany) is focused on development of a quasi-2D model for the prediction of wall temperature profile and coolant temperature , in the problem of coolant flow and wall structure heat transfer in the cooling channels of an liquid rocket engine thrust chamber