Electromagnetic Propulsive Motor

Abstract

The invention comprises an electromagnetic propulsive motor having a rotor capable of rotation around a shaft and having a plurality of radially disposed blades including blade tip portions for compressing a working fluid. The invention further comprises a stator having a case frame, and a plurality of radially disposed vanes extending generally between said case frame and said shaft for directing the working fluid. A plurality of electromagnetic elements disposed within said rotor blades proximate the tip portions thereof interact electromagnetically with a plurality of electromagnetic elements disposed in said stator case frame to drive said rotor.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]The present application claims the benefit of and is a continuation of co-pending U.S. patent application Ser. No. 13 / 109,711 filed May 17, 2011, and entitled “Electromagnetic Propulsive Motor”.FIELD OF THE INVENTION[0002]The present invention relates generally to aircraft propulsion systems, and more particularly to an electromagnetically driven compressive ducted fan propulsion system, herein referred to as an electromagnetic propulsive motor.BACKGROUND OF THE INVENTION[0003]Prior art gas turbine engines often employ a fan to draw in a working fluid, typically air, a compressor to compress the working fluid entering the engine, a combustor to burn the compressed air mixed with fuel, and a turbine that extracts work from the working fluid exiting the engine. Each of the aforementioned engine sections is typically comprised of one or more stages of rotating blades and concomitant vanes to direct the working fluid and extract work from the...

AI Technical Summary

Problems solved by technology

Known gas turbine engines produce large amounts of thrust but are typically costly to operate and manufacture due to the necessity to burn large quantities of jet fuel to drive the turbine.

Additionally, the pollutants produced as a byproduct of jet fuel combustion are undesirable.

Since the gas passing through the engine aft of the combustor is quite hot, all engine components are subjected to tremendous heat.

Furthermore, the rotating components of a gas turbine engine have very high rotational velocities, that, when coupled with thermal expansion and impacts caused by normal engine operation cause them to rub or interfere with the static portions of the turbine.

These inherent features of modern gas turbines render them quite costly to produce, as all components must be produced to extremely tight tolerances and be capable of withstanding enormous thermal and mechanical stresses.

Additionally, many prior art rotor and stator assemblies are quite complex, having a multiplicity of parts required to render the assembly capable of containing a high-pressure air stream and operate under a wide variety of power, speed, and atmospheric conditions.

The cost and complexity of designing and constructing such prior art assemblies is quite prohibitive.

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