General Electric Company

Ge Infrastructure Technology, LLC

Exxonmobil Upstream Research Company

Ge Vernova Infrastructure Technology LLC

General Electric Technology Gmbh

Lucas John Stoia

Patrick Benedict Melton

Richard Martin DiCintio

Timothy James Purcell

Bryan Wesley Romig

Christopher Paul Willis

Thomas Edward Johnson

Donald Mark Bailey

Heath Michael Ostebee

Ronnie Ray Pentecost

Jayaprakash Natarajan

Mohan Krishna Bobba

Elizabeth Leigh Exley

Wei A Chen

Jeffrey Scott LeBegue

James Harold Westmoreland

Keith Cletus Belsom

Russell Pierson DeForest

Charlie Edmond Jones

Jun Cai

Mark William Pinson

Gregory Allen Boardman

Geoffrey David Myers

Ronald James Chila

Christian Xavier Stevenson

Srikanth Chandrudu Kottilingam

Jonathan Dwight Berry

Willy Steve Ziminsky

Emily Klara Happ

Sven Georg Bethke

Jonathan Hale Kegley

Homayoon Feiz

William Michael Poschel

David William Cihlar

Abdul Rafey Khan

Mark Allan Hadley

Predrag Popovic

Robert Joseph Rohrssen

John Charles Intile

Carolyn Ashley Antoniono

John Drake Vanselow

William Francis Carnell, Jr

Seth Reynolds Hoffman

Neal William Grooms

Yimin Huang

Shreekrishna Jayakumar Rao

Dana Morgan

Stanley Kevin Widener

Bruno Schuermans

Baifang Zuo

Sarah Lori Crothers

Hasan Ul Karim

Ilya Aleksandrovich Slobodyanskiy

Kassy Moy Hart

William Lawrence Byrne

Elizabeth Angelyn Fadde

Brandon Taylor Overby

Netaji Haribhau Mane

Kyle Eric Benson

Jonathan Kay Allen

Brandon Lamar Bush

Paula Marie Word

Santiago Yepes

Karthik Subramanian

Shreekrishna Rao

Jeffrey J Hogan

Terese Marinita Martinez

Dwayne Debruhl

Mohammad Fahd Ebna Alam

Kaitlin Marie Neville

Anthony Michael DiNardi

John Bryan Pourcho

Subramanian Annamalai

Crystal McGee McConnaughhay

Nazar Ahmed Elwasila

Jeffrey Scott Lebegue

Richard Martin Dicintio

Russell Pierson Deforest

Wei Chen

Lll James Harold Westmoreland

Patrick Bendict Melton

Mark Allen Hadley

A combustor includes a combustion liner that defines a combustion chamber and an outer sleeve spaced apart from the combustion liner, such that an annulus is defined between the combustion liner and the outer sleeve. The combustor further includes a fuel injection assembly having a boss coupled to at least one of the combustion liner and the outer sleeve. The boss includes an inner flange coupled to the combustion liner, an outer flange, and a body extending between the outer flange and the inner flange. The boss defines a cooling circuit having a post-impingement plenum defined in the inner flange between an inner wall of the inner flange and an impingement plate in cooling proximity to the inner wall; and a plurality of film cooling channels that are defined in the inner flange and fluidly couple the post-impingement plenum to the combustion chamber.

Boss for a fuel injection assembly having cooling circuit and combustor provided therewith

A combustor includes an end cover and at least one fuel nozzle extending from the end cover and at least partially surrounded by a combustion liner. The combustor further includes an outer sleeve spaced apart from and surrounding the combustion liner such that an annulus is defined therebetween. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extending to the fuel injector. A shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The at least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.

Combustor having fuel sweeping structures

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

A system is provided with a fuel sweep system configured to couple to a flow sleeve of a combustor along a first fuel conduit. The flow sleeve is configured to be disposed about a liner of the combustor, and the first fuel conduit is configured to extend along the flow sleeve in a compressor discharge chamber disposed about the flow sleeve. The fuel sweep system includes a first fuel sweep louver adjacent a first fuel sweep opening defined through the flow sleeve.

System and method for sweeping leaked fuel in gas turbine system

A fuel nozzle includes a center body that extends from an upstream end to a downstream end. A nozzle tip, which is fixedly coupled to the downstream end of the center body, includes an outer annular wall that has a forward end and an aft end. A solid aft wall is disposed at the aft end of the outer annular wall. The solid aft wall and the outer annular wall at least partially define a plenum. A nozzle portion, which is disposed within the plenum, includes an inner annular wall and an impingement wall. The impingement wall is spaced apart from the solid aft wall and defines a plurality of apertures configured to direct fluid to impinge upon the solid aft wall. A plurality of outlets is defined in the outer annular wall forward of the solid aft wall to direct post-impingement fluid from the nozzle tip.

Gas turbine fuel nozzle tip comprising an impingement wall

A cartridge tip includes a main body having an outer annular wall and an inner core each extending between a respective upstream end and a respective downstream end. The inner core is radially spaced apart from the outer annular wall such that an annular air passage is defined at least partially between the outer annular wall and the inner core. A pilot fuel circuit extends between a pilot inlet defined in the upstream end of the inner core and a pilot outlet defined in a downstream end of the inner core. The pilot fuel circuit extends at least partially along an axial centerline of the cartridge tip. A main fuel circuit extends between a main inlet in the upstream end of the inner core and a plurality of main outlets circumferentially spaced apart from one another and disposed upstream from the from the pilot outlet.

Cartridge tip for turbomachine combustor

Sealing arrangements and turbomachines are provided. A sealing arrangement includes a transition duct having an upstream end and a downstream end. The transition duct includes an aft frame that circumferentially surrounds the downstream end of the transition duct. A first stage nozzle is spaced apart from the aft frame and defines a gap therebetween. A sealing assembly is coupled to the aft frame. The sealing assembly includes a flexible sealing element that extends from the aft frame, across the gap, to the first stage nozzle. The flexible sealing element is forced into sealing engagement with the first stage nozzle by pressure from a compressed working fluid. The sealing assembly further includes a heat shield disposed between the flexible sealing element and the aft frame. The heat shield terminates within the gap.

Turbomachine sealing arrangement having a heat shield

Combustors and gas turbines are provided. A combustor includes an axial centerline and an end cover. The combustor further includes at least one fuel nozzle that extends from the end cover and at is least partially surrounded by a combustion liner. The combustion liner extends between the at least one fuel nozzle and an aft frame and that defines a combustion chamber. An outer sleeve is spaced apart from and surrounds the combustion liner such that an annulus is defined therebetween. The outer sleeve defines at least one aperture. A wake energizer is mounted on the outer sleeve. The wake energizer defines at least one passage that is angled with respect to the axial centerline of the combustor. The at least one passage aligns and is in fluid communication with the at least one aperture of the outer sleeve.

Combustor having a wake energizer

An insert for an impingement plate and an impingement plate including the insert are disclosed. The impingement plate includes a plurality of cooling holes therein. The insert includes a body including an opening extending longitudinally therethrough. The body also includes a discharge end configured for positioning in an impingement air plenum between the impingement plate and an upstream surface of a combustor cap plate; a flexible insertion end configured for insertion into a respective cooling hole of the plurality of cooling holes; and a fixation element between the discharge end and the flexible insertion end. The fixation element has an outer dimension configured to fixedly couple the body in the respective cooling hole.

Impingement plate with cooling tubes and related insert for impingement plate

A combustor cap assembly, combustor and related method are disclosed. The combustor cap assembly includes: an impingement plate defining a plurality of impingement cooling holes with a first side of the impingement plate in fluid communication with a cooling air plenum. The assembly also includes a combustor cap plate coupled to the impingement plate, such that an impingement air plenum is defined between a second side of the impingement plate and the combustor cap plate. Tubes extend from at least a portion of the plurality of impingement cooling holes at the second side of the impingement plate and extend partially towards the combustor cap plate through the impingement air plenum. The plurality of impingement cooling holes provides for fluid communication between the cooling air plenum and the impingement air plenum through the tubes.

Combustor cap assembly having impingement plate with cooling tubes

A combustor includes at least one fuel nozzle extending from the end cover and at least partially surrounded by the forward casing. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extends to the fuel injector. The fuel injection assembly further includes a shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The shielding assembly includes a venturi nozzle having a circumferentially converging portion and a circumferentially diverging portion. At least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.

An object includes an annular outer body having an end and an interior surface; a first annular inner body disposed inside the annular outer body, the first annular inner body having an exterior surface defining a first annular passage with the interior surface of the annular outer body. The first annular passage includes a first plurality of outlets formed on the end of the annular outer body, the first annular passage receiving a coolant and discharging the coolant adjacent the end of the annular outer body. The object also includes a second annular inner body disposed inside the first annular inner body, the second annular inner body defining a second annular passage with the first annular inner body. Further, the object includes a third annular inner body disposed inside the second annular inner body, with the third annular inner body defining a third annular passage with the second annular inner body; and a fourth annular passage opposite and surrounded by the third annular passage. The object further includes a plurality of suspension elements connecting the interior surface of the annular outer body to the exterior surface of the first annular inner body, each suspension element including a first end connected to a first position on the first inner annular body and a second end connected to a second position on the annular outer body, wherein each first position is angularly circumferentially offset from each second position; and each suspension element is configured to substantially rigidly locate a position of the annular outer body relative to the first annular inner body in axial and lateral directions while permitting controlled deflection in a radial direction wherein the first position of each suspension element is angularly circumferentially offset to provide an imbalanced suspension capable of addressing an imbalanced loading, wherein each suspension element has an at least partially tear-shaped cross-section, and each of the second annular passage, the third annular passage, and the fourth annular passage includes a plurality of outlets formed through the annular outer body, adjacent the end, each of the plurality of outlets for each of the second annular passage, the third annular passage, and the fourth annular passage delivering a gas or fuel adjacent the end of the annular outer body.

Object with tear-shaped suspension for annular bodies

A gas turbine includes a compressor, a turbine, and a combustor disposed downstream from the compressor and upstream from the turbine. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined within the flange and the flange is coupled to an internal face of the end cover. A fuel port is integrally joined with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside of the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.

Integrated fuel nozzle connection

A sealing arrangement includes a transition duct having an aft frame that circumferentially surrounds the downstream end of the transition duct. The aft frame defines a cooling circuit that has an outlet configured to direct cooling air in a radial direction. A first stage nozzle is spaced apart from the aft frame and defines a gap therebetween. A sealing assembly that extend circumferentially along at least a portion of the aft frame and is coupled to the aft frame. The sealing assembly includes a flexible sealing element that extends from the aft frame, across the gap, to the first stage nozzle. The flexible sealing element is forced into sealing engagement with the first stage nozzle by pressure from a compressed working fluid. A cooling flow director that is disposed between the outlet of the cooling circuit and the flexible sealing element.

Turbomachine sealing arrangement having a cooling flow director

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Taylors, SC, United States of America

Lucas John Stoia