A Large Rocket Engine

I had previously proposed rocket engines, this one is a scalable engine optimized for cryogenic propellant, liquid methane and oxygen. These propellants require pre heating for a sustainable combustion. Like in SpaceX Raptor engine, the propellant would be pe burned in order to heat them before combustion. My design puts the pre burner inside the combustion chamber. The objective is to transfer the heat inside the chamber more effectively to the propellent. This design negates the regenerative cooling channels outside the combustion chamber and the rocket nozzle. Allowing much larger combustion chambers than the current rocket engines. The problem with large combustion chambers is that the combustion efficiency decreases with the increase volume. I solve this problem with heat exchanger fins around the pre-burner. When the propellant is heated to auto ignition temperature they burn on contact. Therefore, increased heated surface inside the chamber increases the heat transfer between the gas molecules and the hot metal surface.

The pre burner, the combustion chamber and the nozzle of the engine will be made of Tungsten which has a very high melting point and still a good conductor of heat. There will be no regenerative cooling on the combustion chamber. Therefore, the internal temperature will be kept considerably below the melting point of Tungsten by pumping adequate propellant inside the chamber.

Removal of propellant pipes around the combustion chamber lowers the cost of manufacturing large combustion chambers and reduces the heat stress on the shell of the chamber. Removal of propellant pipes around the nozzle lowers the cost of manufacturing the rocket nozzle and simplifies the gimble mechanism.