MODELLING OF HEAT TRANSFER IN LIQUID PROPELLANT ENGINE WITH REGENERATIVE COOLING METHOD

To some degree, beginning of space era can be considered as the production of human progress in designing and manufacturing liquid propellant engines. All of the first American and Russian launchers used liquid propellant engines that usually use 2 separated components as propellant: oxidizer and liquid fuel. This propellant is stored and maintained separately in some tanks in launch missile and when the rocket turns on it is injected into the combustion chamber and create combustion and buoyancy power. From the very beginning of missile matters, liquid propellant missiles were assigned a special status, and today, countries with this technology invest heavy budgets on R&D for these missiles in military, spatial and research programs.Heat transfer in the thrust chamber is of great importance in the design of liquid propellant rocket engines. If the coolant is one of the propellants, once it passes through the cooling circuit, it can be injected into the combustion chamber or it can be dumped overboard. The former case is referred to as Regenerative cooling system while the latter as dump cooling system. In this papper, the regenerative cooling of a liquid propellant rocket engine has been numerically simulated. RD-106 has been modelled to operate on a LOX/Kerosene mixture at a chamber pressure of 60 bar with 65.8 t thrust and kerosene is considered as the coolant. A numerical investigation was performed to determine the effect of different aspect ratio cooling channels

کلیدواژه ها:

russian engine RD-106 ، Heat transfer ، Regenerative Cooling ، Liquid Oxygen ، Kerosene