General Electric Company

Ethan Patrick O'Connor

Brandon Wayne Miller

Daniel Alan Niergarth

Richard Alan Wesling

Christian Xavier Stevenson

Peter Allen Andrews, Jr

Arthur William Sibbach

John Carl Glessner

David Scott Diwinsky

Sridhar Adibhatla

Alfred Albert Mancini

Ian Francis Prentice

Gert Johannes Van Der Merwe

Wayne Ray Grady

Lawrence William Nurre

Timothy John Sommerer

Michael Edward Eriksen

David Justin Brady

Justin Paul Smith

Barry Lynn Allmon

David Vickery Parker

William James Mailander

John Michael Pyles

Efren Souza Chavez

Nathan Ray Parrott

Alexander Thomas Hills

John Robert Holland

A hybrid electric gas turbine engine is provided. The hybrid electric gas turbine engine includes: a turbomachine having a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath, the turbomachine defining a core air flowpath exhaust; and an electric machine assembly having an electric machine disposed aft of the core air flowpath exhaust and mechanically connected to the turbine section.

Electric machine assembly

A turbine engine having an engine core that includes a compressor section, a combustion section, and a turbine section. An inner cowl circumscribes the engine core and an outer cowl radially spaced from the inner cowl, circumscribes at least a portion of the inner cowl. A transfer gearbox, at least partially located within an inner cowl space between the engine core and the inner cowl, operably couples to a first accessory device. An accessory gearbox located in the outer cowl operably couples to the transfer gearbox and a second accessory device.

Turbine engine including transfer gearbox and accessory gearbox

A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Accessory gearbox for a turbine engine

A fuel delivery system for a gas turbine engine includes a fuel source; a draw pump downstream of the fuel source for generating a liquid fuel flow from the fuel source; a main fuel pump downstream of the draw pump; and a fuel oxygen reduction unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen reduction unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture, wherein the contactor receives an inlet fuel flow from the draw pump; a separator in fluid communication with the contactor, the separator receives the fuel/gas mixture and separates the fuel/gas mixture into an outlet stripping gas flow and an outlet fuel flow at a location upstream of the main fuel pump; a catalyst disposed downstream of the separator, the catalyst receives and treats the outlet stripping gas flow, wherein a stripping gas stream flows out the catalyst; and a water removal component disposed between the catalyst and the contactor, wherein the water removal component removes water from the stripping gas stream.

Fuel oxygen conversion unit with integrated water removal

A fuel oxygen reduction unit assembly for a fuel system is provided. The fuel oxygen reduction unit assembly includes: a fuel oxygen reduction unit located downstream from the fuel source and defining a stripping gas flowpath and a liquid fuel flowpath, the fuel oxygen reduction unit comprising a means for transferring an amount of oxygen from a liquid fuel flow through the liquid fuel flowpath to a gas flow through the stripping gas flowpath; and an oxygen conversion unit in flow communication with the stripping gas flowpath configured to extract a flow of oxygen from a gas flow through the stripping gas flowpath, the oxygen conversion unit defining an oxygen outlet configured to provide the extracted flow of oxygen to an external system.

Fuel delivery system having a fuel oxygen reduction unit

A fuel delivery system for a gas turbine engine includes a fuel tank; a draw pump downstream of the fuel tank for generating a liquid fuel flow from the fuel tank; a main fuel pump downstream of the draw pump; and a fuel oxygen conversion unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen conversion unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture; and a dual separator pump in fluid communication with the contactor for receiving the fuel/gas mixture and separating the fuel/gas mixture into a stripping gas flow and the liquid fuel flow at a location upstream of the main fuel pump.

Fuel oxygen conversion unit with a dual separator pump

A gearbox assembly includes a first gear coupled to a first shaft, a second gear coupled to a second shaft, and a plurality of planet gears that mesh with the first gear and the second gear. The first shaft includes a first shaft stiff portion and a first shaft flexible portion that includes a greater flexibility than a flexibility of the first shaft stiff portion such that the first gear moves in a radial direction. The second shaft includes a second shaft stiff portion and a second shaft flexible portion that includes a greater flexibility than a flexibility of the second shaft stiff portion such that the second gear moves in the radial direction. The first gear and the second gear move to distribute loads substantially equally on the plurality of planet gears.

Gearbox assembly

A fuel oxygen reduction unit for an engine is provided. The fuel oxygen reduction unit includes an inlet fuel line; a stripping gas source; a contactor selectively in fluid communication with the stripping gas source, the inlet fuel line, or both to form a fuel/gas mixture; and a separator that receives the fuel/gas mixture, the separator configured to separate the fuel/gas mixture into an outlet stripping gas flow and an outlet fuel flow; wherein a flow of stripping gas passes through the fuel oxygen reduction unit a single time.

Fuel oxygen reduction unit for prescribed operating conditions

Methods of and apparatus for monitoring the health of a fuel oxygen conversion unit for a vehicle or a vehicle engine are provided. For example, a method comprises providing a distribution of sensed values obtained from a plurality of sensors distributed along an axial length of a gas oxygen reduction unit of the fuel oxygen conversion unit and determining the health of the fuel oxygen conversion unit from the distribution. As another example, a fuel oxygen conversion unit defines a circulation gas flowpath from a fuel gas separator to a contactor and comprises a gas oxygen reduction unit positioned in the circulation gas flowpath for reducing an oxygen content of a flow of stripping gas through the circulation gas flowpath. A plurality of sensors are distributed along an axial length of the gas oxygen reduction unit.

Methods and apparatus for monitoring health of fuel oxygen conversion unit

A fuel oxygen conversion unit for a vehicle or an engine of the vehicle includes a contactor; a mechanically-driven, first fuel gas separator defining a liquid fuel outlet and a stripping gas outlet, the fuel oxygen conversion unit defining a liquid fuel outlet path in fluid communication with the liquid fuel outlet of the first fuel gas separator; and a second fuel gas separator positioned in fluid communication with the liquid fuel outlet path at a location downstream of the first fuel gas separator.

Fuel oxygen conversion unit

The present disclosure is directed to an optical adapter for an optical scope. The optical scope includes a tube defining a conduit. The optical adapter is coupled to an end of the tube. The optical adapter defines a proximate end and a distal end. The optical adapter includes a casing defining a longitudinal direction. The casing includes a first wall and a second wall, in which the first wall and the second wall define a first viewing port therebetween. The second wall defines a second viewing port. The optical adapter further includes a hinge coupled to the first wall, a reflecting lens defining a first end separated from a second end in the longitudinal direction, in which the first end is coupled to the hinge, and an actuator coupled to the first wall and to the second end of the reflecting lens. The actuator pivots the reflecting lens about the hinge from a retracted position adjacent to the first wall to an extended position toward the second wall.

Integrated variable view optical adapter for an optical scope

A method of operating a fuel oxygen reduction unit for a vehicle or a gas turbine engine of the vehicle is provided. The fuel oxygen reduction unit including a contactor and a fuel gas separator, and further defining a stripping gas flowpath in flow communication with a stripping gas inlet of the contactor and a stripping gas outlet of the fuel gas separator. The method includes receiving data indicative of a parameter of a stripping gas flow through the stripping gas flowpath or of a component in flow communication with the stripping gas flow through the stripping gas flowpath; and determining an operability condition of the fuel oxygen reduction unit, or a component operable with the fuel oxygen reduction unit, based on the data received indicative of the parameter of the stripping gas flow or of the component in flow communication with the stripping gas flow.

Fuel oxygen reduction unit control system

In one exemplary embodiment of the present disclosure, a method of operating a fuel system for an aeronautical gas turbine engine is provided. The method includes: providing a flow of fuel to a fuel nozzle of the aeronautical gas turbine engine during a wind down condition; operating a fuel oxygen reduction unit to reduce an oxygen content of the flow of fuel provided to the fuel nozzle of the aeronautical gas turbine engine during the wind down condition; and ceasing providing the flow of fuel to the fuel nozzle of the aeronautical gas turbine engine, the fuel nozzle comprising a volume of fuel after ceasing providing the flow of fuel to the fuel nozzle; wherein operating the fuel oxygen reduction unit comprises operating the fuel oxygen reduction unit to reduce an oxygen content of the volume of fuel in the fuel nozzle to less than 20 parts per million.

Fuel oxygen reduction unit

A fuel oxygen conversion unit includes a contactor; a fuel gas separator, the fuel oxygen conversion unit defining a circulation gas flowpath from the fuel gas separator to the contactor; and an isolation valve in airflow communication with the circulation gas flowpath for modulating a gas flow through the circulation gas flowpath to the contactor.

Growing community of inventors

Hamilton, OH, United States of America

Ethan Patrick O'Connor