General Electric Company

Ge Infrastructure Technology, LLC

Other

Haier US Appliance Solutions, Inc.

Thomas Edward Johnson

William David York

Willy Steve Ziminsky

Jong Ho Uhm

Christian Xavier Stevenson

Baifang Zuo

Heath Michael Ostebee

Benjamin Paul Lacy

Christopher Paul Keener

Geoffrey David Myers

Kaitlin Marie Graham

Patrick Benedict Melton

Jonathan Dwight Berry

Lucas John Stoia

Stanley Kevin Widener

Jason Thurman Stewart

Johnie Franklin McConnaughhay

Kevin Weston McMahan

Kwanwoo Kim

Abdul Rafey Khan

Lewis Berkley Davis, Jr

Bryan Wesley Romig

Carl Robert Barker

Ronald Scott Bunker

Gregory Allen Boardman

Michael John Hughes

Gilbert Otto Kraemer

Dale M Brown

Kevin Sean Matocha

Peter Micah Sandvik

Joel Meier Haynes

James Thomas Brown

Jeremy Clyde Bailey

Joseph Vincent Citeno

John Charles Intile

Jayaprakash Natarajan

Yimin Huang

Billy T Fowler

Scott Robert Simmons

James Harold Westmoreland

Mark Stewart Schroder

Robert Joseph Rohrssen

Thomas Frank Fric

John Joseph Lipinski

Shiva Kumar Srinivasan

James Christopher Monaghan

John Drake Vanselow

Jeffrey Bernard Fedison

David Andrew Helmick

Wei Zhao

Kara Johnston Edwards

Robert Paul Ziegler

Larry Lou Thomas

Mark Roger Brown

Christopher Mordaunt

Anne Elizabeth Kolman

Daniel Gerritt Wegerif

Stefan Maier

Benjamin Paul Lacey

John Brandon MacMillan

Chrisophter Paul Keener

Alicia Johnson

Wessam Sherif Estefanos

Geoffrey David Meyers

Jr Lewis Berkley Davis

A fuel injection assembly for a combustor of a gas turbine engine includes a body with a head section that defines an air intake chamber. A mixing chamber is disposed below the air intake chamber. A deflection member is disposed in the air intake chamber and includes an upper deflection surface and sides spaced apart from inner wall surfaces of the air intake chamber such that peripheral air passages are defined for air to pass from the air intake chamber into the mixing chamber. A plurality of radially extending and longitudinally spaced-apart ribs is disposed along longitudinal side walls of the mixing chamber. A fuel plenum is disposed along the longitudinal side walls of the mixing chamber, and a plurality of fuel injection holes is defined from the fuel plenum through the longitudinal side walls of the mixing chamber and at least some of the ribs.

Fuel injection assembly for a combustor

A vibration damper for a fuel conduit of a gas turbine combustor includes a mounting portion and a damping portion. The mounting portion is secured to the fuel conduit, and the damping portion includes a stack of damping washers, a bushing on top of the stack of damping washers, a spring clip secured around the stack of damping washers and the bushing, and a shoulder bolt disposed through the bushing and the stack of damping washers and engaged to the mounting portion.

Vibration damper for fluid conduit of gas turbine combustor

An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.

Torch igniter for a combustor

The present disclosure is directed to a fuel nozzle including a center body having a tube shape and a ring manifold disposed at an aft end of the center body. The fuel nozzle also includes an inner tube extending axially through the ring manifold and disposed within the center body. The inner tube is in fluid communication with a diluent supply. The fuel nozzle further includes a fuel tube extending helically around a portion of the inner tube. The fuel tube fluidly couples a fuel plenum of the ring manifold to a liquid fuel supply. Furthermore, the fuel nozzle includes a plurality of fuel injectors circumferentially spaced within an outer band of the ring manifold and in fluid communication with the fuel plenum. Each fuel injector is oriented to direct atomized liquid fuel radially outward from the center body. The ring manifold and the inner tube are thermally decoupled.

Dual-fuel fuel nozzle with gas and liquid fuel capability

An inlet manifold includes a main inlet oriented along a first direction and a pilot inlet oriented along a second direction perpendicular to the first direction. A wye passage includes an inlet branch in fluid communication with the main inlet. The inlet manifold also includes a first main passage in fluid communication with a first outlet branch of the wye passage and a second main passage in fluid communication with a second outlet branch of the wye passage. The first main passage extends generally along the first direction between the wye passage and a first main outlet. The second main passage extends generally along the first direction between the wye passage and a second main outlet. The inlet manifold also includes a pilot passage in fluid communication with the pilot inlet. The pilot passage extends generally along the first direction between the pilot inlet and a pilot outlet.

Fuel nozzle, fuel supply assembly thereof, and method of assembling a fuel nozzle

An annular fuel manifold includes an annular fuel plenum defined within the annular fuel manifold, an axial inlet into the annular fuel plenum, and a deflector downstream of the axial inlet, the deflector oriented such that fluid flow into the annular fuel plenum from the axial inlet is deflected by the deflector at least partially along a circumference of the annular fuel plenum.

Annular fuel manifold with a deflector

A dual-fuel fuel nozzle includes a centerbody that at least partially defines an air plenum therein. A tip body is disposed at a downstream end of the centerbody. The tip body includes an upstream side that is axially spaced from a downstream side. The downstream side defines a circular slot and a circular recess that is positioned radially inwardly from the circular slot. The circular recess includes a floor and a side wall, The floor defines an insert opening and the side wall defines an annular groove that includes an undercut surface. The tip body further defines a plurality of orifices annularly arranged around the insert opening radially inward from the side wall of the circular recess. Each orifice includes an inlet that is in fluid communication with the air plenum and an outlet that is oriented towards the undercut surface.

Dual-fuel fuel nozzle with liquid fuel tip

The present disclosure is directed to a dual-fuel fuel nozzle that includes a center body having a tube shape and a gas fuel plenum defined within the center body. The duel-fuel fuel nozzle also includes a ring manifold defining a liquid fuel plenum disposed within the center body. The duel-fuel fuel nozzle further includes a plurality of radially oriented fuel injectors in fluid communication with the liquid fuel plenum. Additionally, the duel-fuel fuel nozzle includes an inner fuel tube extending axially within the center body. A portion of the inner fuel tube extends helically about an axial centerline of the center body. The inner fuel tube is in fluid communication with an axially oriented fuel injector. Furthermore, the duel-fuel fuel nozzle includes first fuel tube extending helically around a portion of the inner fuel tube within the center body. The first fuel tube is fluidly coupled to the fuel plenum.

A premixing fuel nozzle assembly for a turbomachine is disclosed as having at least one fuel injector with an outer jacket having a first end and a second end and a threaded surface disposed therebetween. The first end has a cylindrical sealing surface and the second end has at least one wrenching pocket. An annular hub is disclosed as having an aperture with a first end and a second end and a threaded surface disposed therebetween, wherein the aperture is configured to at least partially house the fuel injector therein and the annular hub further has a conical seat about the first end. The fuel injector cylindrical sealing surface swages inward to form a hermetic seal when contacting the annular hub conical seat as the fuel injector is threaded into the aperture.

Aerodynamic fastening of turbomachine fuel injectors

The present disclosure is directed to a dual-fuel fuel nozzle including a center body having a tube shape and a gas fuel plenum defined within the center body. The fuel nozzle also includes a plurality of turning vanes extending radially outward from the center body. Each turning vane includes at least one fuel port in fluid communication with the gas fuel plenum. A plurality of apertures is disposed through the plurality of turning vanes. The fuel nozzle further includes a ring manifold disposed within the center body downstream of the plurality of turning vanes. Additionally, the fuel nozzle includes a first fuel tube extending helically around a centerline of the center body. Furthermore, the fuel nozzle includes an air shield disposed within the center body and extending circumferentially around the first fuel tube.

Dual-fuel fuel nozzle with air shield

The present disclosure is directed to a nozzle assembly including a header manifold and a ring manifold, which defines a liquid fuel plenum, spaced from the header manifold. An outer sleeve connects to the ring manifold, and a nozzle body connects to the outer sleeve. The ring manifold, the outer sleeve, and the nozzle body define a fluid chamber. An inner fuel tube extends from the header manifold to the nozzle body. A portion of the inner fuel tube extends helically about an axial centerline of the nozzle assembly between the ring manifold and the nozzle body. A first fuel tube extends helically around a portion of the inner fuel tube. The first fuel tube fluidly couples the liquid fuel plenum to the header manifold. A second fuel tube extends helically around a portion of the inner fuel tube and fluidly couples the liquid fuel plenum to the header manifold.

Nozzle assembly for a dual-fuel fuel nozzle

A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a fuel injector including an outer jacket having a first end and a second end with a threaded surface disposed therebetween. The first end of the fuel injector may include a cylindrical sealing surface. The fuel nozzle assembly also may include an annular hub including an aperture having a first end and a second end with a threaded surface disposed therebetween. The aperture may be configured to at least partially house the fuel injector therein and includes a conical seat about the first end. The cylindrical sealing surface may swage inward along the conical seat to form a seal therebetween as the liquid fuel injector is threaded into the aperture.

Systems and methods for creating a seal about a liquid fuel injector in a gas turbine engine

The present application provides a combustor for use with a gas turbine engine. The combustor may include a primary stage nozzle in communication with a linear actuator and a number of stationary secondary nozzles surrounding the primary stage nozzle in whole or in part. The linear actuator varies the position of the primary stage nozzle with respect to the stationary secondary nozzles.

Multi-stage combustor with a linear actuator controlling a variable air bypass

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Greer, SC, United States of America

Thomas Edward Johnson