General Electric Company

Precision Combustion, Inc.

Ge Infrastructure Technology, LLC

Ge Vernova Infrastructure Technology LLC

General Electric Technology Gmbh

Jonathan Dwight Berry

Michael John Hughes

Kevin Weston McMahan

Thomas Edward Johnson

Jason Thurman Stewart

Stanley Kevin Widener

Hasan Ul Karim

Russell Pierson DeForest

Carl Robert Barker

Clay Thomas Griffis

Gilbert Otto Kraemer

Subir Roychoudhury

James Scott Flanagan

Heath Michael Ostebee

Gregory Scott Means

Chunyang Wu

Kara Johnston Edwards

Geoffrey David Myers

Victor John Morgan

Neelesh Nandkumar Sarawate

Deepak Trivedi

Abdul Rafey Khan

Ibrahim Sezer

Abhijit Som

Srikanth Chandrudu Kottilingam

Patrick Benedict Melton

Matthew Troy Hafner

William David York

Jong Ho Uhm

Richard Mastanduno

Steven Charles Woods

Ashok Kumar Anand

Derrick Walter Simons

Keith Cletus Belsom

Johnie Franklin McConnaughhay

James Anthony West

Mark Allan Hadley

Mark Carmine Bellino

Bruce Crowder

Sam David Draper

Robert Joseph Rohrssen

Joseph Vincent Citeno

Jesse Ellis Barton

David Lang Spence

James Christopher Monaghan

John Drake Vanselow

Maxim Lyubovsky

Wei Zhao

Patrick Shane Riley

Bailey Basso

Lewis Berkley Davis, Jr

Lucas John Stoia

Gregory Allen Boardman

Willy Steve Ziminsky

Kwanwoo Kim

Baifang Zuo

Constantin Dinu

Donald Mark Bailey

Krishna Kumar Venkataraman

Christopher Paul Keener

Kaitlin Marie Graham

Charles Van Buchan

Archie Lee Swanner, Jr

Bradley Donald Crawley

Anthony Wayne Krull

John Joseph Lipinski

Timothy James Purcell

Almaz Kamilevich Valeev

Garth Curtis Frederick

Theodore R Strickland

Homayoon Feiz

James Thomas Brown

Girard Albert Simons

Gilbert O Kraemer

Brandon Lamar Bush

Luis Flamand

Jerome Walter Goike

Daniel Gerritt Wegerif

Glenn David Nelson

Richard F Keyser

Gilbert Otto Kramer

Timur Rustemovich Repikov

Elizabeth Iola Paasche

Emily Kaufman

Sven Bethke

Ronald James Chila

Michael John Highes

Kevin Weston Mcmahan

Russell Pierson Deforest

Luis M Flamand

Fuel injection assemblies and combustors are provided. The fuel injection assembly includes a fuel injector that is configured to couple to an outer sleeve of the combustor. The fuel injection assembly further comprises a boss that is spaced apart from the fuel injector and is configured to couple to a combustion liner of the combustor. The boss includes a flange portion, an annular wall portion extending from the flange portion, and an interior surface. The boss defines a serpentine cooling passage that extends from an inlet on the flange portion to an outlet on the interior surface.

Fuel injection assembly having a boss with a serpentine cooling passage

A bundled tube fuel nozzle assembly for a gas turbine combustor includes: a forward plate facing a head end air plenum, an aft plate facing a combustion chamber, and premixing tubes extending from the forward plate to the aft plate. An interior side wall extends circumferentially around the first plurality of premixing tubes and defines an interior fuel plenum, and an exterior side wall extends circumferentially around the interior side wall and defines an exterior fuel plenum. Both side walls extend axially from the forward plate to the aft plate. The interior fuel plenum is in fluid communication with the exterior fuel plenum. Each premixing tube includes at least one fuel injection hole therethrough, which is in fluid communication with the interior fuel plenum. The head end air plenum is in fluid communication with the combustion chamber, via inlet ends of the premixing tubes.

Bundled tube fuel nozzle assembly for gas turbine combustor

A gas turbine engine combustor includes: a head end section containing a fuel nozzle assembly and defining a head end air plenum; and a liner extending downstream from the head end section toward an aft frame and defining a combustion chamber therein. First injectors are disposed at a first axial location spaced apart from the head end section to direct a first fuel/air mixture through the liner. A dynamics mitigation system includes cold-side resonators disposed wholly within the head end air plenum, each resonator of the plurality of cold-side resonators having a resonator body with a closed end and an open neck extending from the resonator body opposite the closed end. Each resonator body defines a respective volume, and the open neck is in fluid communication with the head end air plenum. In some embodiments, quarter-wave tube dampers are installed within the fuel nozzle assembly of the head end section.

Gas turbine combustor with dynamics mitigation system

Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a boss that forms at least a portion of an annular wall. The annular wall defines a mixing channel that extends along a center axis. The fuel injection assembly further includes a fuel injector that has a radially outer wall and a radially inner wall that at least partially defines a fuel plenum. The fuel injector further includes a plurality of premix tubes that each extend along an injection axis from an inlet end on the radially outer wall through the fuel plenum to an outlet end, and wherein the injection axis is slanted towards the center axis of the mixing channel.

Fuel injection assembly for a combustor

Stacked cooling assemblies and combustor bead ends are provided. A stacked cooling assembly includes an inlet plate defining an inlet to a coolant circuit, an outlet plate defining an outlet of the coolant circuit, and an intermediate plate disposed between the inlet plate and die outlet plate. The intermediate plate defines an intermediate cavity. A downstream surface of the inlet plate, an upstream surface of the outlet plate, and the intermediate cavity collectively define a connecting channel that fluidly couples the inlet to the outlet.

Stacked cooling assembly for gas turbine combustor

An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment, the combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The combustion liner defines a cavity forward of the turbine nozzle. The cavity extends between the first side wall and the second side wall. An impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members configured to direct coolant to impinge upon the first side wall and the second side wall. Each impingement member extends from a respective inlet defined within the flange to a respective closed end. A plurality of impingement apertures are defined on each impingement member.

Impingement cooling apparatus for turbomachine

An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The integrated combustor nozzle further includes an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall. The impingement cooling apparatus further includes stand-offs extending from each impingement member of the plurality of impingement members. The stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces.

Impingement cooling apparatus support structure and method of manufacture

A turbomachine component is provided. The turbomachine component formed from an additive manufacturing system. The additive manufacturing system defines an axial build direction, a radial direction, and a circumferential direction. The turbomachine component includes an exterior portion. The exterior portion includes a first end wall, a second end wall, and an outer band extending axially between the first end wall and the second end wall. The turbomachine component further includes an interior portion disposed within the exterior portion. The interior portion includes a self-breaking inner band extending axially between the first end wall and the second end wall. The self-breaking inner band includes a plurality of teeth disposed between the first end wall and the second end wall.

Turbomachine component having self-breaking supports

A bundled tube fuel nozzle is provided. The bundled tube fuel nozzle includes a first end wall, a second end wall, an outer band that extends between the first end wall and the second end wall, and an inner band that extends between the first end wall and the second end wall. The inner band is disposed within the outer band. A bellows wall is disposed between the inner band and the outer band. The bellows wall surrounds the inner band such that a first fuel plenum is defined annularly between the inner band and the bellows wall. The inner band defines a second fuel plenum that is in fluid communication with the first fuel plenum via one or more apertures defined in the inner band. A plurality of tubes extends in an axial direction between the first end wall and the second end wall within the second fuel plenum.

Combustor having thermally compliant bundled tube fuel nozzle

A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum and that define injection holes therethrough. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. The mixing conduits fluidly couple the high-pressure plenum to the main passage, and the fluid from the fluid plenum is delivered with the high-pressure fluid to the main passage, where the fluids mix before being discharged from an outlet of the main passage. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.

Fluid mixing apparatus using high- and low-pressure fluid streams

A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.

Curved seal for adjacent gas turbine components

Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.

Fuel injection assembly for a turbomachine

An integrated combustor nozzle includes a combustion liner that extends between an inner liner segment and an outer liner segment along a radial direction. The combustion liner including a forward end portion, an aft end portion, a first side wall, and a second side wall. An impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement apertures that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel includes an inlet portion that extends from the impingement plate to a collection duct. The impingement panel further includes a plurality of supports spaced apart from one another. The plurality of supports extend between, and are coupled to, the inlet portion, the collection duct, and the impingement plate.

Impingement panel support structure and method of manufacture

Sealing arrangements and rotor assemblies are provided. A sealing arrangement includes a stationary component, a rotating component spaced apart from the stationary component. A clearance is defined between the stationary component and the rotating component. The sealing arrangement further includes a plurality of magnets embedded within the rotating component. The sealing arrangement further includes a brush seal having a frame and a plurality of magnetically responsive filaments. The plurality of magnetically responsive filaments each extending from the frame to a free end. The plurality of magnetically responsive filaments are attracted to the rotating component by the plurality of magnets. The plurality of magnetically responsive filaments at least partially covering the clearance, such that a flow of fluid across the clearance is restricted.

Turbomachine clearance control using brush seals having magnetically responsive filaments

Integrated combustor nozzles and turbomachines are provided. An integrated combustor nozzle includes a cooling insert having a flange. The cooling insert further includes a first wall and a second wall that each define respective passages therein. The first wall and the second wall each extend from an open end defined within the flange to a closed end. The first wall and the second wall each include an impingement side spaced apart from a solid side. Each impingement side defines a plurality of impingement apertures configured to direct coolant from the respective passage towards a side wall of the combustion liner. The cooling inserts further includes a collection passageway that is defined between the solid sides of the first wall and the second wall.

Cooling insert for a turbomachine

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Simpsonville, SC, United States of America

Jonathan Dwight Berry