Magnetic advanced generation jet electric turbine
View Patent ↗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 exo-skeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation over traditional gas turbine technology today. 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.
1. A shaftless gas turbine engine comprising:
a. an outer casing of generally cylindrical shape and having a first end, a second end and a length, wherein the outer casing provides the load bearing surface of the engine;
b. a nozzle section within the first end of the outer casing;
c. a turbine section within the outer casing between the nozzle section and the second end, wherein the turbine section includes a plurality of electromagnetically segmented multi-stage power turbine levitation coils;
d. a combustor section within the outer casing between the turbine section and the second end;
e. a compressor section within the outer casing between the combustor section and the second end, wherein the compressor section includes a plurality of multi-stage segmented compressor levitation coils;
f. a bypass fan section within the outer casing between the compressor section and the second end, wherein the bypass fan section includes a plurality of dual counter rotating bypass fan magnetic coils;
g. an inlet section within the second end of the outer casing; and
h. 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 passing through the nozzle section, the turbine section, the combustor section, the compressor section and the bypass fan section, wherein the hollow core is configured to allow ambient air to pass through, without being subject to action by any of the nozzle section, the turbine section, the combustor section, the compressor section and the bypass fan section,
wherein the inlet section is configured to deliver a portion of incoming air from the second end into the hollow core and a portion into the bypass fan section and 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 located at the electromagnetically segmented multi-stage power turbine levitation coils, the multi-stage segmented compressor levitation coils and the dual counter rotating bypass fan magnetic coils, respectively.
2. The gas turbine engine of claim 1 wherein the bypass fan section includes 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.
3. The gas turbine engine of claim 1 wherein the compressor section includes a plurality of turbine blade pairs, wherein the turbine blade pairs are magnetically levitated by pairs of permanent magnets.
4. The gas turbine engine of claim 1 wherein the nozzle section includes a magnetohydrodynamic accelerator configured to ionize gas from the combustor section.
5. The gas turbine engine of claim 1 wherein the magnetohydrodynamic accelerator includes a series of ring accelerator induction electrode plates.