Magnetic advanced generation jet electric turbine

Abstract

Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exoskeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions.

What is claimed is: 
     
         1 - 13 . (canceled) 
     
     
         14 . A shaftless gas turbine engine comprising:
 a. an outer casing of generally cylindrical shape and having an inlet section, wherein the outer casing provides a load bearing surface of the engine;   b. a hollow core within a center of the outer casing establishing a shaftless section of the outer casing and extending the length of the outer casing wherein the hollow core is configured to allow ambient air to pass therethrough;   c. a turbine section within the outer casing;   d. a compressor section within the outer casing; and   e. a bypass fan section with dual bypass fans within the outer casing arranged to propel bypass air around the turbine section,   wherein the turbine section, the compressor section and the bypass fan section are maintained in position within the outer casing by magnetic levitation air bearings.   
     
     
         15 . The gas turbine engine of  claim 14  wherein the dual bypass fans include two alternating rows of bypass fan blades and diffuser blades, wherein there are bypass fan blades closest to the compressor section and closest to the inlet section. 
     
     
         16 . The gas turbine engine of  claim 14  wherein the compressor section includes a plurality of turbine blade pairs, wherein the turbine blade pairs are magnetically levitated by pairs of permanent magnets. 
     
     
         17 . The gas turbine engine of  claim 14  further comprising a nozzle section and a combustor section, wherein the nozzle section includes a magnetohydrodynamic accelerator configured to ionize gas from the combustor section. 
     
     
         18 . The gas turbine engine of  claim 17  wherein the magnetohydrodynamic accelerator includes a series of ring accelerator induction electrode plates.