Hydrogen-fueled supersonic turboramjet engine

A Hydrogen-Fueled Supersonic Turboramjet Engine system comprising:

• an inlet;
• a combustor;
• a fuel storage;
• a high-pressure turbine, and a low-pressure turbine;
• a compressor;
• a first plurality of stream lines configured to circulate a fuel through a first plurality of heat exchangers, wherein the first plurality of stream lines connects the fuel storage to the combustor;
• and
• a second plurality of stream lines configured to circulate a working fluid through a second plurality of heat exchangers, including the first plurality of heat exchangers, at least some positioned in airframes and a precooler, wherein the second plurality of stream lines connects the compressor to the low-pressure and the high-pressure turbines.

A method of operating a Hydrogen-Fueled Supersonic Turboramjet Engine to be able to fly at supersonic speed up to Mach 5 while developing adequate thrust for subsonic flights comprising the steps of:

• bringing the engine to a supersonic speed of a first Mach number greater than 1.0 prior to initial thrust is provided by the engine;
• igniting the engine and accelerating to a greater Mach number greater than the first Mach number;
• decelerating to a Mach number less than 1.0 and providing thrust from the engine for controlled flight;
• wherein the engine comprises:
• an inlet;
• a combustor;
• a fuel storage;
• a high-pressure turbine and a low-pressure turbine wherein the initial pressure of the high-pressure turbine is greater than the initial pressure of the low-pressure turbine;
• a compressor operably attached to the low-pressure turbine;
• and
• a plurality of stream lines configured to circulate cryogenic LH2 fuel through a plurality of heat exchangers positioned in airframe and a precooler, wherein the plurality of fuel stream lines connects the fuel storage to the low-pressure and high-pressure turbine and the combustor.