Tangential turbofan propulsion system
OwnerRobert Bado, Artem Madatovinventors
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Abstract
The present invention is a turbofan propulsion system, based on a tangential gas turbine that is structurally a part of the propulsion system's centrifugal compressor, wherein the gas turbine's combustion chambers with nozzles are placed to rotate around a larger radius circle at a supersonic circumferential speed, and the fan blades are placed to rotate around a smaller radius circle at a subsonic circumferential speed, therefore increasing the efficiency of the propulsion system.
Claims8
A turbofan propulsion system based on a rotary gas turbine of tangential type, comprising a fan with a plurality of at least two blades for capturing and moving air, driven by the gas turbine, a rotor with a plurality of at least two fuel combustion chambers with De Laval-type nozzles, a plurality of at least two fuel channels with injectors supplying liquid fuel to the said combustion chambers equipped with spark plugs, an axial dual-stage compressor with oblique blades, characterized in that the said compressor is structurally integrated with the said rotor, and is connected to the said combustion chambers, wherein the second air compression stage of the said dual-stage compressor, comprising a plurality of at least two radial channels mechanically connected to the said rotor, and connected by their inward facing ends with the first axial stage of the said compressor, and by their outward facing ends connected with the said fuel combustion chambers located on the said rotor's periphery.
Dependencies are inferred from the claim text.