Integrated bypass turbojet engines for air craft and other vehicles

A turbojet engine comprising:

• a turbojet housing structure with an air intake and a common jet ejection nozzle,
• a rotor disk unit having a fan unit with a fan portion and a peripheral turbine portion, the fan portion having fan blades with internal centrifugal compressor cells with openings to the air intake and the turbine portion having turbine blades extending from the fan blades, the turbine blades having internal passages communicating with the compressor cells and having radial open tips wherein the rotor disk unit has fuel channels to the internal passages of the turbine blades, wherein fuel injected into the turbine blades cools the compressed air and turbine blades, and,
• a peripheral combustion chamber around the radial tips of the turbine blades constructed to direct combustion gases back around to the turbine blades with at least one fuel injector and nozzles that discharge combustion gases between turbine blades of the rotor disk unit wherein air that bypasses the combustion chamber flows through the fan unit between the fan blades cooling air flow compressed in the centrifugal compressor cells that with fuel injected into the turbine blades is radially ejected into the combustion chamber from the tips of the turbine blades, wherein combustion gases passing between the turbine blades mix with the bypass air passing between the fan blades in the common jet ejection nozzle.