Analysis of the effect of flux penetrating the wall temperature in the Regenerative Cooling cryogenic Combustion chamber

Liquid rocket engine design, combustion due to high temperatures and high rates of heat transfer (1MW / m2 to about 160MW / m2) of hot gases to the chamber walls, the cooling thrust chamber of the utmost importance. The thrust chamber cooling design, selection of appropriate methods, design and related topics thrust chamber cooling ducts, double glazing and thermal coating is very important. Liquid propellant engine in the wall of the combustion chamber and nozzle is necessary in order to prevent the failure of a cooling system used engine block resistance. Cooling the refrigerant recovery method (usually fuel) through channels for which it is embedded in the engine block and passed through the engine block reduces the temperature. Modeling and analysis of fluid flow channels in the engine cooling liquid propellant because of the high heat flux one of the most important and most challenging issue in the context of this type of engine. That's why in this article cooling channel recovery numerical simulation is a liquid propellant engine. The engine is fed with cryogenic cooling and cryogenic propellant as the cooling fluid is intended.to increase or decrease the amount of flux is not.