Gm Global Technolgoy Operations, Inc.

Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Daimler Chrysler Ag

Daimlerchrysler Corporation

Donald Klemen

Michael Roland Schmidt

Alan G Holmes

Eric E Wilson

James D Hendrickson

Henryk Sowul

Brendan M Conlon

Anthony H Heap

Gregory A Hubbard

Larry T Nitz

Michael James Armstrong

Ahmed Mostafa El-Antably

Russell E White

James Allen Raszkowski

Edward Claude Rice

Douglas David Dierksmeier

James P Ordo

Grantland I Kingman

Bradley Eugene Auker

Brian Scott Maners

Steven Wesley Tomlinson

John R Bitner

Christine A Ross

Norman K Bucknor

John A Diemer

Boris Iosifovich Burgman

Arthur Hall, Iii

Reece R Fuehrer

Patrick C Sweeney

Erik Alexander Munevar

Richard A Pashnik

Joseph H Hunter

James C Polak

Geoffrey L Gatton

Robert Keith Dunlap

Dennis M Cooke

Mark Boden

Steven R McMullen

Richard L Wagner

Jonathan Terrell

J Thomas Craig

George Gerald Shafer, Jr

Christine AH Ross

In some examples, propulsion, electrical generation, and cooling system. The system comprises a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a first fluid, wherein a portion of the compressed first fluid is directed out of the bleed air outlet to define bleed air from the compressor. The system also includes a turbo-generator including a combustor, wherein the combustor is configured to receive the bleed air from the compressor and combust a fuel with the bleed air, wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor. The system also includes an air cycle cooling system configured to remove heat via an air cycle cooling process, wherein the air cycle cooling process is charged via the bleed air from the compressor. A compressor of the air cycle cooling system may be driven by a turbine of the turbo-generator or a turbine of the gas turbine engine.

Bleed air charged cooling system with turbo-generator

A vertical takeoff and landing aircraft system includes a gas turbine engine coupled to a variable pitch propeller. The gas turbine engine is also coupled to a power split device including a first motor generator, a second motor generator, and a planetary module therebetween. The planetary module includes a sun gear, a ring gear, and a planet carrier. The motor generators are coupled to inverters, a DC bus and a battery. The battery is configured to power balance fans disposed on wings and horizontal stabilizers of the aircraft system. The balance fans can be closed off after vertical lift has been achieved.

Electrically controlled vertical takeoff and landing aircraft system and method

An electromagnetic clutch assembly may include a first clutch plate, a second clutch plate, and a synchronizer. The second clutch plate may define an aperture. A portion of the synchronizer may be configured to extend through the aperture. In the absence of a magnetic field, the first clutch plate and the first surface of the second clutch plate may define an air gap and the portion of the synchronizer may extend into the air gap. In response to a first magnetic field, the portion of the synchronizer may contact the first clutch plate. In response to a second magnetic field, the portion of the synchronizer may translate in the aperture toward the second clutch plate and the first clutch plate and the second clutch plate may close the air gap.

Synchronized electromagnetic single plate clutch system

In some examples, an electromagnetic clutch assembly. The assembly includes a pair of clutch plates including a first clutch plate configured to rotate around a rotational axis; and a second clutch plate configured to rotate around the rotational axis. The assembly further includes an electromagnetic coil circumferentially surrounding the air gap, wherein the electromagnetic coil is configured to generate a magnetic flux passing through the first clutch plate and the second clutch plate, wherein the pair of clutch plates define an air gap between the first clutch plate and the second clutch plate in the absence of the magnetic flux, and wherein the magnetic flux is configured to cause at least one of the first clutch plate or the second clutch plate to move to close the air gap.

Electromagnetic clutch system

A lightweight lift system for VTOL/VSTOL operation running in parallel with an existing turbine. This system distributes LP power by switching compressor flow and fuel proportionally over to the lift turbine module. As forward thrust is demanded, some of the power is transitioned back to the flight LP turbine, which can drive a variable propeller, fan or can supply jet thrust. As flight motion occurs, the power to the lift fan can be reduced to zero and lift closed off.

Lightweight parallel combustion lift system for vertical takeoff aircraft

A rotor of an electric machine includes a main rotor body having a longitudinal axis, the main rotor body comprising: a hollow cylinder body with a first end and a second end; an integral end flange at the first end; a separate end flange disposed at the second end of the cylinder body; and laminations disposed on an outer surface of the cylinder body, the laminations comprising magnetic material.

Electric machine rotor

A gas turbine engine and methods of operation include a low pressure electric motor-generator arranged for selective operation in a generator mode to generate electrical power or a drive mode to assist rotation of a low pressure drive shaft of the engine.

Low pressure generator for gas turbine engine

A turbofan gas turbine engine includes low pressure (LP) motor-generator operable in either a generation mode or a drive mode, an high pressure (HP) motor-generator operable in a either a generation mode or a drive mode, and a power control module for selectively operating the LP and HP motor-generators according to operational conditions of the engine.

Control of low pressure generator for gas turbine engine

In examples, a propulsion and electrical generation system including a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a fluid, wherein a portion of the compressed fluid is directed out of the bleed air outlet to define bleed air from the compressor; and a turbo-generator including a combustor, wherein the combustor includes a fuel inlet and a bleed air inlet, wherein the bleed air inlet is in fluid communication with the bleed air outlet from the compressor, wherein the combustor is configured to receive the bleed air via the bleed air inlet from the bleed air outlet of the gas turbine engine and receive fuel via the fuel inlet, wherein the combustor is configured to combust the received fuel with the received bleed air, wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor.

Electrical energy generating system

A gearbox rigidly coupled to a static structure; a driven component rigidly coupled to another static structure; a clutch assembly floating between and coupled to the gearbox and driven component. The clutch may have aligned output and input shafts, defining an engagement surface, a bearing, and a magnetic friction plate coupled and rotating with the input shaft. The plate may have a friction-engagement face, and a magnetic flux generator. The magnetic flux generator may be rigidly coupled to a static housing and partially surrounded in the radial direction by a structure configured to reduce leakage of a magnetic flux, by defining a plurality of voids, which direct multiple passes of the magnetic flux through the engagement surface of the output shaft. The magnetic flux generator may create the magnetic flux that creates a magnetic force between the engagement face and the magnetic friction plate that causes them to engage.

Electromagnetic clutch for gas turbine accessories

A gas turbine engine and methods of operation include a low pressure electric motor-generator having an electrical assembly for electrical connection.

Low pressure generator with electrical assembly for gas turbine engine

A high-Mach engine includes a gas turbine core, an inlet assembly, and a transmission. The inlet assembly including an inlet turbine and the transmission configured to couple the inlet turbine and a core turbine of the gas turbine core cooperate to control air moving through the high-Mach engine.

Inlet turbine and transmission for high-mach engines

A thermal management system for a pulse load on an aircraft. The thermal management system utilizing the reserve fuel from the aircraft to create thermal capacitance such that the instantaneous capacity of the cooling system to remove heat from the aircraft may be sized less than the rate of heat generated by the pulsed load (e.g. laser, radar, rail gun etc.) The reserve fuel is maintained at a temperature in a reservoir and cooled via a cooling system. Fuel from the reservoir is selectively mixed with fuel exiting the pulsed load heat exchanger to provide fuel to the inlet of the heat exchanger at a predetermined temperature, the temperature based at least upon the heat generated by the laser, flow rate of fuel and efficiency of the heat exchanger.

Fuel thermal capacitance for pulsed platform loads

An inlet assembly for a high-mach engine includes a gas turbine core, an inlet turbine, and a core-flow director. When in a closed position, the core-flow director forces air to interact with the inlet turbine before entering the gas turbine core.

Inlet turbine for high-mach engines

Growing community of inventors

Carmel, IN, United States of America

Donald Klemen