Abstract: A gas turbine engine which includes an outer casing; a central longitudinal hollow shaft with a forward air inlet; a three stage rotating superconducting electric bypass fan with front and rear fan blades and a diffuser blade interposed between said front and rear fan blades wherein the diffuser blade rotates in an opposite direction to the front and rear fan blades; a multiple stage superconducting axial compressor positioned aft of the three stage rotating superconducting electric bypass fan; a multiple stage superconducting electric turbine core positioned aft of the multiple stage variable speed superconducting axial compressor, whereby the electric power from the multiple stage superconducting electric turbine core powers the three stage superconducting electric bypass fan and the multiple stage superconducting axial compressor.

Abstract: A gas turbine engine which includes an outer casing; a central longitudinal hollow shaft with a forward air inlet; a three stage rotating superconducting electric bypass fan with front and rear fan blades and a diffuser blade interposed between said front and rear fan blades wherein the diffuser blade rotates in an opposite direction to the front and rear fan blades; a multiple stage superconducting axial compressor positioned aft of the three stage rotating superconducting electric bypass fan; a multiple stage superconducting electric turbine core positioned aft of the multiple stage variable speed superconducting axial compressor, whereby the electric power from the multiple stage superconducting electric turbine core powers the three stage superconducting electric bypass fan and the multiple stage superconducting axial compressor.

Abstract: HYPERDRIVE receives continuous air breathing assistance from compressed atmospheric air through a high speed magnetically core driven turbine accelerator which resolves around a common flow path tunnel. The tunnel runs from the front to the back of the engine. It is assisted by a series of radial geometric ramjet engines that share the common flow path tunnel for hypersonic exhaust but has separate inlet air from a linear aerospike which governs mass flow of air, velocity of inlet air and pressure to the turbine and/or ramjets, as well as the positioning of the shock wave at the inlet to reduce aerodynamic drag. The ramjet is of hybrid engine design where it can also function as a scramjet, thus a ram-scramjet structure for combustion in a radial configuration about the engine (aft of an electrical compressor), where the common flow path tunnel also serves as a compression tunnel to compress air through a the constantly occurring series of compression shocks entering from and around the aerospike.

Abstract: A gas turbine rotor having a combination of proximal embedded permanent magnets in the blended turbine(s) trunnion structure to which blades are integral to and through these distal trunnion channels attach to which turbine blades are integral to as a single component is provided. Permanent magnets or warm conducting coils or cold superconducting coils can be used. The structure rotates around a superconducting power shaft core (SPSC), running axially in relation to the turbine blade permanent magnets, for example, and embedded distal trunnion rings.

Abstract: An aerospace hybrid hypersonic propulsion system which has a common core airflow path through the engine combining subsonic, transonic, supersonics and hypersonic propulsion system and architecture in such a way that five known engine cycles known in the art are configured and connected to operate seamlessly with a hybrid electric and thermal cycle.

Abstract: A gas turbine engine which includes an outer casing; a central longitudinal hollow shaft with a forward air inlet; a three stage rotating superconducting electric bypass fan with front and rear fan blades and a diffuser blade interposed between said front and rear fan blades wherein the diffuser blade rotates in an opposite direction to the front and rear fan blades; a multiple stage superconducting axial compressor positioned aft of the three stage rotating superconducting electric bypass fan; a multiple stage superconducting electric turbine core positioned aft of the multiple stage variable speed superconducting axial compressor, whereby the electric power from the multiple stage superconducting electric turbine core powers the three stage superconducting electric bypass fan and the multiple stage superconducting axial compressor.

Abstract: A turbine assembly system and apparatus for a Hyperjet™ and method for making same is provided. Specifically, the turbine assembly provides a power generation system for a turbine engine and includes a plurality of stages. Each stage of the turbine assembly includes a stator having a wire distributed winding; and a rotatable blisk that encircle the stator with an air gap disposed therebetween. The rotatable blisk includes a rotor disk and a plurality of blades that extend radially outward from the rotor disk. The rotor disk includes six superconducting magnets positioned in a circular arrangement within the rotor disk to encircle the stator. An electromagnetic field providing high power and power density is generated between the superconducting magnets and the stator with the blisk rotates about the stator during engine operation.

Abstract: A supersonic aircraft having unique structural, geometrical, electromagnetic, mechanical, thermal and aerodynamic configuration is described. Its design characteristics maximize aerodynamic performance, speed, efficiency, comfort and range in the operational affect of carrying passengers over long distances at very high flight speeds and Mach numbers, generally above Mach 4.0+. It has fully integrated-mated fuselage twin engine nacelle structures which reduce and stabilize wave drag, wherein engines sit forward of the sonic boom electrode swept aerospace but are integrated right through the sub-wing, the aero-spike and inlet just above the top surface of the central wing, and above and the major wing mating join, attached via a massive composite titanium keel structure, through the central wing box and fuselage.

Abstract: HYPERDRIVE receives continuous air breathing assistance from compressed atmospheric air through a high speed magnetically core driven turbine accelerator which resolves around a common flow path tunnel. The tunnel runs from the front to the back of the engine. It is assisted by a series of radial geometric ramjet engines that share the common flow path tunnel for hypersonic exhaust but has separate inlet air from a linear aerospike which governs mass flow of air, velocity of inlet air and pressure to the turbine and/or ramjets, as well as the positioning of the shock wave at the inlet to reduce aerodynamic drag. The ramjet is of hybrid engine design where it can also function as a scramjet, thus a ram-scramjet structure for combustion in a radial configuration about the engine (aft of an electrical compressor), where the common flow path tunnel also serves as a compression tunnel to compress air through a the constantly occurring series of compression shocks entering from and around the aerospike.

Abstract: A turbine assembly system and apparatus for a Hyperjet™ and method for making same is provided. Specifically, the turbine assembly provides a power generation system for a turbine engine and includes a plurality of stages. Each stage of the turbine assembly includes a stator having a wire distributed winding; and a rotatable blisk that encircle the stator with an air gap disposed therebetween. The rotatable blisk includes a rotor disk and a plurality of blades that extend radially outward from the rotor disk. The rotor disk includes six superconducting magnets positioned in a circular arrangement within the rotor disk to encircle the stator. An electromagnetic field providing high power and power density is generated between the superconducting magnets and the stator with the blisk rotates about the stator during engine operation.

Abstract: A gas turbine turbine rotor(s) having a combination there of proximal embedded permanent magnets in the blended turbine(s) trunion structure to which blades are integral to and through these distal trunion channels attach, to which turbine blades are integral to as a single component, thereof exist permanent magnet) or in another embodiment warm conducting coils, or cold superconducting coils) levitating fields, rotating around a superconducting power shaft core (SPSC), running axially in relation to said turbine blade magnets and embedded distal trunion rings.

Abstract: Disclosed is a high-power, fully-superconducting electric machine and major subcomponents including a dual (twin) superconducting, counter rotating, sub-scale bypass fan machine, 13-stage switched reluctance turbo-motor, electric compressor, annular ion-plasma combustor with electromagnetic electrodes, and a five stage superconducting counter-rotating turbine power generation machine which is capable of developing 2.5 MW per stage.

Abstract: Disclosed herein is a hybrid electric, turbine-powered, all wheel drive automotive platform or truck/military platform design that utilizes a hybrid electromagnetic segmented gas turboshaft engine, whereby all rotating turbomachinery components are segmented from one another electromagnetically. In some embodiments, the components may be levitated in magnetic bearings. In this way, the turbine stages have superconducting ring generators circumferentially surrounding the turbine core generating multi-megawatts of electric power for the land automotive platform. The hybrid turbine acts as an integrated superconducting generator. A plurality of electromagnetic transmission(s) connect to all-wheel drive wheel armatures that are adjacent to the superconducting stators in each wheel, which drive the wheels. Each wheel may be an electric powered-magnetic powered hybrid drive-energy storage unit architecture itself.

Abstract: A supersonic aircraft having unique structural, geometrical, electromagnetic, mechanical, thermal and aerodynamic configuration is described. Its design characteristics maximize aerodynamic performance, speed, efficiency, comfort and range in the operational affect of carrying passengers over long distances at very high flight speeds and Mach numbers, generally above Mach 4.0+. It has fully integrated-mated fuselage twin engine nacelle structures which reduce and stabilize wave drag, wherein engines sit forward of the sonic boom electrode swept aerospace but are integrated right through the sub-wing, the aero-spike and inlet just above the top surface of the central wing, and above and the major wing mating join, attached via a massive composite titanium keel structure, through the central wing box and fuselage.

Abstract: A superconducting integrated ring turbine motor generator gas turbine engine stage of the present invention includes a combination of turbine vanes, rotors and blisk assemblies that prevent temperatures during operation from interfering with the extraction or control of power generation processes. The engine stage includes a ring having an evenly spaced array of aerodynamic vanes affixed on the inside or outside of the ring. The vanes are spaced apart by a nonmagnetic armature assembly spacer ring.

Abstract: An integrated hybrid electric power generation system for producing jet thrust, a superconducting direct drive turbine ring motor for vertical lift, multi-megawatt electric current generation and a pulse-phased high power directed energy weapon (DEW). The system is managed electrically, and may be mated directly to a magnetic aerodynamic generation of rotorhead optimized control as a direct drive electric lift-jet thrust rotorcraft system (DDELJTRS) manifesting an all flight managed controls and weaponized electric system in rotorcraft, vertical lift, aerodynamic flight control, directed energy weapon and jet propulsion for forward flight high speed cruise.

Abstract: A rotorcraft having an operational range and a plurality of rotor blades, each rotor blade capable of assuming an angular pitch, utilizes a control apparatus a mechanism for independently controlling an angular pitch value of each of the plurality of rotor blades wherein a collective sum of the angular pitch values of the plurality of rotor blades is not constant over the operational range of the rotorcraft.

Abstract: With turbine segments controlled electrically in a shaftless design, the turbine of the present invention creates high propulsion efficiencies over a broader range of operating conditions through the integration of gas turbine, electric and magnetic power systems, advanced materials and alternative petroleum-based combustion cycles.

Abstract: A wind generator is disclosed in which superconducting ring generators are utilized without the need for a load bearing drive shaft and other mechanical components, decreasing overall weight and enabling the use of variable geometry blades for increased overall efficiency.

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.