Methane engine for rocket propulsion

A methane engine for rocket propulsion, comprising:

• a gas generator mixing methane supplied from a methane gas supply pipe and an oxidizer supplied from an oxidizer branch supply pipe, and jetting and igniting the methane gas;
• a turbine generating driving force using a methane gas flame generated from the gas generator;
• a methane supply pump coaxially fixed to the turbine for supplying methane in a liquid state stored in a methane storage tank to a methane supply pipe;
• an oxidizer supply pump coaxially fixed to the turbine for supplying the oxidizer stored in an oxidizer storage tank to an oxidizer supply pipe;
• and
• a combustor receiving the methane and the oxidizer supplied from the methane supply pump and the oxidizer supply pump through the methane supply pipe and the oxidizer supply pipe, and igniting and jetting the methane gas to provide propulsive force to a projectile, selected from the group consisting of a rocket, a missile, and a space shuttle,
• wherein the methane supply pipe is branched into a nozzle supply pipe and a combustion supply pipe, the nozzle supply pipe supplies the methane to a nozzle cooling channel installed on the outer surface of a nozzle of the combustor so that the methane is discharged to a nozzle transfer pipe to perform the regenerative cooling of the nozzle, and the combustion supply pipe supplies the methane to a combustion chamber cooling channel installed on the outer surface of a combustion chamber of the combustor so that the methane is discharged to a combustion chamber transfer pipe to perform the regenerative cooling of the combustion chamber, so that the regenerative cooling of the nozzle and the regenerative cooling of the combustion chamber are independently performed.