General Electric Company

General Electric Company Polska Sp. Z O.o.

General Electric Deutschland Holding Gmbh

Ge Avio S.r.l.

General Electric Company Deutschland Holding Gmbh

Darek Tomasz Zatorski

Kurt David Murrow

Andrew Breeze-Stringfellow

Brandon Wayne Miller

Christopher Charles Glynn

Randy M Vondrell

Daniel Alan Niergarth

Jeffrey Donald Clements

Mohamed Osama

Alan Roy Stuart

Richard Ludwig Schmidt

Dominic L Barone

Gert Johannes Van Der Merwe

Peeyush Pankaj

Shashank Suresh Puranik

Glenn David Crabtree

Matthew Ryan Polakowski

John Russell Yagielski

Richard Alan Wesling

Bhaskar Nanda Mondal

Christopher James Kroger

Ian Francis Prentice

Patrick Michael Marrinan

Tsuguji Nakano

Justin Paul Smith

Jeffrey Anthony Hamel

Donald Scott Yeager

Nicholas Rowe Dinsmore

Maciej Krzysztof Grunwald

Bartłomiej Drozd

Ching-Pang Lee

Thomas Ory Moniz

Paul Robert Gemin

Nathan Evan McCurdy Gibson

Craig William Higgins

David Marion Ostdiek

Matteo Renato Usseglio

Richard David Cedar

Adam Tomasz Paziński

Roberto Maddaleno

Leszek Marek Rzeszutek

Jeffrey Raymond Menard

Patrick John Lonneman

Miroslaw Czarnik

Andrea Piazza

Jan Christopher Schilling

David William Crall

Atanu Saha

Syed Arif Khalid

Donald Albert Bradley

Philip Michael Cioffi

Joseph George Rose

Juraj Hrubec

Brian Alan Norton

Ramana Reddy Kollam

Adam Tomasz Pazinski

Joseph Robert Dickman

Joel Francis Kirk

Andrea Depalma

Antonio Giuseppe D'Ettole

Pablo Gabriel Piazza Galarza

Trevor Wayne Goerig

Craig Miller Kuhne

Brendan Michael Freely

Fabian Isaza

Michael Beverley

Bartlomiej Drozd

Luca Giacobone

Jia Xiaochuan

Rangasai Madoor Comandore

Samuel Jacob Martin

Miroslaw Sobaniec

Mirosław Czarnik

Andrew Michael Watson

John Edward Altman

Marek Szrajer

Jakub Jan Broniszewski

Humphrey Martin Wills

Alessandra Torri

Vaibhav Deshmukh M

Raymond Anthony Humble

A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.

Hybrid-electric propulsion system equipped with a coupler for switching between modes of operation

A turbomachine is provided. In one aspect, the turbomachine includes a rotating component and an electric machine that includes a stator assembly and a rotor assembly rotatable with the rotating component relative to the stator assembly. Further, the turbomachine includes an actuator coupled with the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both relative to one another. In addition, the turbomachine includes a controller configured to receive data indicating an operating state of the rotating component and cause the actuator to adjust a position of at least one of the stator assembly and the rotor assembly based at least in part on the operating state of the rotating component.

Gas turbine engine equipped with a control system for management of rotor modes using an electric machine

An electric machine is provided. The electric machine defines a centerline and includes: a stator assembly; a rotor assembly rotatable relative to the stator assembly about the centerline; and an actuator coupled to the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both along the centerline between a first position and a second position, the rotor assembly positioned closer to the stator assembly when in the first position than when in the second position.

Electric machine

An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.

Electrical machines for integration into a propulsion engine

An electric machine having a hybrid insulative-conductive manifold is disclosed. In one aspect, an electric machine includes a manifold that includes an insulative plate and a conductive backplate positioned adjacent to the insulative plate. The insulative plate and the backplate define a first channel and a second channel therebetween. The electric machine also includes a prime winding and a secondary winding electrically isolated from the prime winding. The prime winding and the secondary winding are both in fluid communication with the first channel and the second channel. A terminal conductor extends through the backplate and insulative plate and is electrically coupled with the prime winding. The terminal conductor is electrically isolated from the backplate and provides cooling fluid to the prime winding and the first channel so that cooling fluid flows between the terminal conductor and the prime winding and between the terminal conductor and the first channel.

Electric machine having a hybrid insulative-conductive manifold

A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.

Inlet for unducted propulsion system

An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.

Vertical takeoff and landing aircraft

An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.

Unducted thrust producing system architecture

The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.

Method and system for integrated pitch control mechanism actuator hydraulic fluid transfer

A turbomachine equipped with an embedded electric machine having a segmented and movable stator is provided. In one aspect, a turbomachine defines a radial direction and includes a rotating component, actuators, and an electric machine. The electric machine includes a rotor assembly rotatable with and operatively coupled with the rotating component. The electric machine also includes a stator assembly having a stator split into stator segments. Each one of the stator segments is movable by one of the actuators between a first position and a second position along the radial direction, the stator segments each being closer to the rotor assembly along the radial direction when in the first position than when in the second position.

Turbomachine equipped with an embedded electric machine having a segmented and movable stator

A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and is driven by the input shaft. A component of the gear assembly drives the output shaft. The gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

Gearbox configurations for clockwise and counterclockwise propeller rotation

There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.

Gas turbine engines with improved guide vane configurations

A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

Turbine engine having a balance cavity

An electric machine for a drive system having a first DS rotor and a second DS rotor includes a first EM rotor rotatable about an axis in a first circumferential direction and including a plurality of magnets, the first EM rotor configured for mechanical coupling to the first DS rotor; and a second EM rotor rotatable about the axis in a second circumferential direction and including a plurality of windings, the second EM rotor configured for mechanical coupling to the second DS rotor and the plurality of magnets of the first EM rotor operably engaged with the plurality of windings of the second EM rotor.

Dual rotor electric machine

Growing community of inventors

Fort Wright, KY, United States of America

Darek Tomasz Zatorski