General Electric Company

Other

Craig Douglas Young

Bernard Patrick Bewlay

Bangalore Aswatha Nagaraj

Steven Clayton Vise

Apostolos Pavlos Karafillis

Paul Vincent Arszman

John Frederick Ackermann

Eva Zielonka Lanman

Nicole Justis

Paul James Ogden

Gilbert Farmer

Ronghai Qu

John Michael Kern

Leonardo Ajdelsztajn

Daniel Dale Brown

Thomas Anthony Leen

Jonathan Harry Kerner

Paul Edward Sabla

Ronald T Murach

Ella Christine Kutter

Christopher Charles Glynn

Clayton Stuart Cooper

Perumallu Vukanti

James Thompson

Donald Michael Corsmeier

Ann Melinda Ritter

John Alan Manteiga

Karthikeyan Sampath

Reed Roeder Corderman

Scott Roger Finn

Douglas Roy Forman

Herbert Kopecek

Brandon Stephen Good

Allen Michael Danis

Wei Wu

Mark Willard Marusko

Joshua L Miller

Laurent Cretegny

Nicholas Ryan Overman

Kenneth Edward Seitzer

Raymond William Heidorn

Lynn Ann DeRose

Donald Lee Gardner

Huageng Luo

Kevin S O'Hara

Gurunath Gandikota

Donald Scott Yeager

Thomas John Tomlinson

David Bruce Patterson

Jeffrey Carl Mayer

David Allen Kastrup

Kiyoung Chung

An-Ping Zhang

David Perveiler

Peter David Toot

Glenn Edward Wiehe

Marwan Al-Roub

Peter Michael Finnigan

Mayank Krisna Amble

Eric Dean Jorgensen

Fred Sharifi

Janet Sue Bennett

Daniel Louis Depperschmidt

Melissa Suzanne Sander

Fazila Seker

Michael Orlando Cimini

Dean P Modroukas

Courtney Ann Kiszewski

Mohammad Ehteshami

Kyle Earl Roland Henry

Deborah Anne Schorr

Steve Steffens

Anthony Hazlett

Walter Byron Houchens, Iii

Michael Joseph Zerbe

Tom Compton

Johannes Eckstein

Gregory Alan Richardson

Lee Roy LaPierre

Morgan Frederic Intrator

James Nelson Bratton

Dane Anthony Elliott-Lewis

Shixue Wen

Magdi N Azer

Walter Byron Houchens Iii

Deborah A Schorr

Bangalore Aswartha Nagaraj

Nicole Barbara Justis

Paul V Arszman

Kyle Earl Henry

Kevin Swayne O'Hara

Joshua Leigh Miller

A component for a turbine engine may be formed by spraying particulate with a nozzle toward a substrate. The particulate may be deposited to form one or more annular layers and a reinforcing structure. The component may be a closed loop annular component having a reinforcing structure of specific dimensions enabled by the methods described.

Cold spray duct for a gas turbine engine

A high-speed, air-breathing propulsion engine includes an inlet configured to compress incoming air, a fuel injector configured to supply a fuel for mixing with the compressed incoming air to form a fuel-air mixture, and a combustor configured to burn the fuel-air mixture. The combustor includes a rotation detonation combustor system and a bluff body system that cooperate to generate thrust.

Airbreathing propulsion engines including rotating detonation and bluff body systems

A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.

Gas turbine combustor fuel injector flow device including vanes

A method and apparatus for separating particles from an inlet airflow of a turbine engine has a centerbody with a radially outer scavenge conduit. The inlet airflow has entrained particulate matter, which can impact an impact surface defining part of the centerbody. The impact surface can be disposed at an angle or have a low coefficient of restitution to reduce the velocity of the incoming particulate matter. The particulate matter is radially diverted radially outward through the scavenge conduit, unable to make a turn defined by the shape of the centerbody.

Inlet particle separator for a turbine engine

A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.

Combustion system and method of assembling the same

A gas turbine engine system comprising, a gas turbine engine including a combustion area, a laser, a fuel nozzle including an optical fiber operative to transmit light emitted from the laser to the combustion area, the optical fiber also transmitting a fuel into the combustion area, wherein the light is operative to ignite the fuel in the combustion area.

Systems involving fiber optic igniters transmitting fuel and laser light

An engine mount structure is provided with active vibration mechanisms which are attached in the vicinity of the engine mount to prevent engine vibrations from propagating into the engine mounting structure, for example, the wing or fuselage structure of an aircraft. Additionally, sensors are provided on the engine and/or wing/fuselage structure to provide control signals to the active vibration mechanisms so that the active vibration mechanism react to the sensed data to minimize the vibration transmissibility from the engine into the wing/fuselage.

Active cancellation and vibration isolation with feedback and feedforward control for an aircraft engine mount

An electrical generator for extraction of electrical power from a gas turbine engine includes a rotor portion and a stator portion disposed within a booster cavity of the gas turbine engine. The rotor portion is rotatably supported about the stator portion. The stator portion rigidly is supported within the booster cavity. The rotor portion has a plurality of poles circumferentially arranged opposite the stator portion. The stator portion includes a plurality of coil portions disposed about an outer periphery of the stator portion adjacent to the stator portion. The stator and rotor portions are configured to generate electrical power when the rotor portion is rotated about the stator portion by a shaft of the gas turbine engine to induce electrical currents in the coil portions. The electrical generator extracts electric power from the turbine engine to supplement primary electrical generation sources of the engine.

Integrated boost cavity ring generator for turbofan and turboshaft engines

A device includes a first thermally conductive substrate having a first patterned electrode disposed thereon and a second thermally conductive substrate having a second patterned electrode disposed thereon, wherein the first and second thermally conductive substrates are arranged such that the first and second patterned electrodes are adjacent to one another. The device includes a plurality of nanowires disposed between the first and second patterned electrodes, wherein the plurality of nanowires is formed of a thermoelectric material. The device also includes a joining material disposed between the plurality of nanowires and at least one of the first and second patterned electrodes.

Thermal transfer and power generation devices and methods of making the same

A wireless-enabled tightening system for fasteners is disclosed. The system includes a visual designator configured to project an indicator onto a workpiece. The system also includes a torque wrench comprising a wireless transmitter and a means for identifying whether the correct torque has been applied to a fastener on the workpiece and configured to provide a feedback for a user. The system also includes a camera configured to capture an image of the workpiece when an appropriate amount of torque has been applied to the fastener. The system further includes a microprocessor for determining sequence of the fastener and identifying the tightened fastener.

Method for operating a torque system configured to tighten a series of fasteners

A fan containment casing includes a core comprising a number of tows. The core has a central region and two end regions. The tows are grouped into a number of bands and form a number of filament-wound radially disposed layers. The bands of tows are interleaved as a number of direct bands and indirect bands along at least a portion of one or more of the layers. A method of forming a fan containment casing includes winding a number of tows on a liner to form a number of radially disposed layers, where each of the layers is continuously connected to at least one adjacent one of the layers across one of the end regions via at least one of the tows.

Fan containment casings and methods of manufacture

An inside out generator disposed aft of the low-pressure turbine spool to generate power for the electrical demands of an aircraft system. The low-pressure turbine discharge flow is used to drive the power turbine, which is coupled to the generator. The generator is able to extract power at idle conditions of the aircraft engine from ducting the discharge through the inside out generator. The system eliminates the placement of a generator in the hot gas path of the discharge, and enables the injection of power directly to the accessory gear box of the engine.

Electric power generation using power turbine aft of LPT

A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slots are formed in at least one of the annular portions. The outer annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of outer radial members connecting the outer annular portion and the middle annular portion are provided between adjacent windows therein. Similarly, the inner annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of inner radial members connecting the inner annular portion and the middle annular portion are provided between adjacent windows therein. The cowl further includes a plurality of circumferentially spaced stiffening ribs, where each stiffening rib includes: a middle portion including a rear edge configured to substantially conform to a forward surface of the middle annular portion so that an area extending between the forward and rear edges is upstream of the middle annular portion; an outer portion including a forward edge configured to conform to a rear surface of the outer annular portion; and, an inner portion including a forward edge configured to conform to a rear surface of inner annular portion. The middle rib portion further includes a forward edge configured to extend through the radial slots when positioned in the middle annular portion, whereas the inner and outer rib portions further include a rear edge configured to extend through the radial slots when positioned in the inner and outer annular portions. Each stiffening rib is then connected to the inner, outer and middle annular portions.

Fabricated cowl for double annular combustor of a gas turbine engine

A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a centerbody. The surface reflects radiation back into the hot gas flow path or into the atmosphere. The reflected radiation is not focused onto any other hardware component. The design of the component is such that the radiation is returned to the gas flow path or sent to the atmosphere rather than absorbed into a component wall that only serves to increase the temperature of the wall.

High temperature centerbody for temperature reduction by optical reflection and process for manufacturing

Growing community of inventors

Maineville, OH, United States of America

Craig Douglas Young