A liquid fueled rocket engine converts energy stored in propellants into a means for generating thrust. This specific design will convert the chemical energy stored in the molecular bonds of compressed gaseous oxygen and liquid kerosene into thermal energy through combustion. The pressure driven flow will then convert some of the available thermal energy into kinetic energy, which will transition the flow from subsonic through sonic to supersonic speeds. This supersonic flow generates a reaction force that will propel the rocket engine in the opposite direction of the flow of the supersonic gasses.
To accomplish tasks above various components were theoretically designed, manufactured, and assembled. These components include: the propellant feed system, an injector, combustion chamber, nozzle, cooling jacket, and ignition system. The feed system is what would be used to transport the propellants from storage to the inlet of the injector. The injector will be used to introduce the propellant into the combustion chamber and properly mix the propellant and oxidizer for combustion. The combustion chamber is a large tube where the propellants chemical energy is converted into thermal energy which is used in the nozzle, the portion of the design where the flow area varies, in order to increase the kinetic energy of the propellant. The cooling jacket is used to run water over the entire system to convectively remove heat from the copper structure to prevent high temperature. Lastly, the ignition system is what is used to begin the combustion reaction by introducing the necessary activation energy to start the chemical reaction.