Document Type : Scientific extension


1 Member of the Faculty of Technical Engineering, Islamic Azad University, Chalus Branch, Chalus, Iran

2 Student of Islamic Azad University, Ayatollah Amoli branch

3 Master's degree, Islamic Azad University, Firuzkoh Branch, Tehran, Iran


In liquid rocket engine design, because of the combustion due to the 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 is of utmost importance. Also, the thrust chamber cooling design, the selection of appropriate methods, as well as the design and topics related to thrust chamber cooling ducts, double glazing and thermal coating are very important. Liquid propellant engine in the wall of the combustion chamber and nozzle is a necessary part in order to prevent the failure of a cooling system using engine block
resistance. In this paper, the combustion process is investigated using a computational fluid dynamics method. To do this, first the similar works in the field are reviewed and then the equations that exist for this process are extracted to determine what equations need to be solved. By examining this method, it was determined that the chosen numerical method could be used to solve the combustion equation. Finally, the simulation results for the geometry in different fluxes are studied which led to acceptable outcomes.


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