General Electric Company

Meritor Heavy Vehicle Technology, LLC

Exxonmobil Upstream Research Company

Arvin Meritor Technology, LLC

Arvin Technologies, Inc.

Patrick Benedict Melton

Lucas John Stoia

Richard Martin DiCintio

James Harold Westmoreland

David William Cihlar

Gregory Allen Boardman

Robert Joseph Rohrssen

Thomas Edward Johnson

Ronald James Chila

Russell Pierson DeForest

Christopher Paul Willis

John Drake Vanselow

Bryan Wesley Romig

Donald Mark Bailey

Carolyn Ashley Antoniono

Benjamin Paul Lacy

Willy Steve Ziminsky

Gilbert Otto Kraemer

Wei A Chen

Christian Xavier Stevenson

Kwanwoo Kim

Jeffrey Scott LeBegue

Ertan Yilmaz

William Lawrence Byrne

William Michael Poschel

Jonathan Dwight Berry

Abdul Rafey Khan

William David York

Scott Robert Simmons

James Scott Flanagan

Keith Cletus Belsom

Ronnie Ray Pentecost

Balachandar Varatharajan

Timothy James Purcell

Matthew Paul Berkebile

Donald Timothy Lemon

Kyle Lee Kidder

Jerome David Brown

Kevin Weston McMahan

Stanley Kevin Widener

Baifang Zuo

Jong Ho Uhm

Zhaoli Hu

Sarah Lori Crothers

David Leach

Ilya Aleksandrovich Slobodyanskiy

Mark Allan Hadley

Predrag Popovic

John Charles Intile

Jack Darrin Oates

Jesse Ellis Barton

Jack R McKenzie

Bradley Donald Crawley

Mohan Krishna Bobba

Jonathan Hale Kegley

Elizabeth Angelyn Fadde

William Francis Carnell, Jr

David Kenton Felling

Brandon Taylor Overby

Jonathan Kay Allen

Kyle Eric Benson

Luis Flamand

John Alfred Simo

Kevin Woodlock

Erich Daniel Charters

Christine Elaine Simu

An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell.

Assembly for controlling clearance between a liner and stationary nozzle within a gas turbine

A bundled tube fuel nozzle includes a forward plate, a first intermediate plate and an outer sleeve defining a fuel plenum, a second intermediate plate axially spaced from the first intermediate plate where the first intermediate plate, the second intermediate plate and the outer sleeve define a purge air plenum, an aft plate axially spaced from the second intermediate plate where the second intermediate plate, the aft plate and the outer sleeve define a cooling air plenum and an annular wall that extends from the second intermediate plate to the aft plate. The annular wall defines a cooling flow channel within the bundled tube fuel nozzle. A plurality of apertures is defined proximate to a cool side of the aft plate and provide for fluid communication between the cooling flow channel and the cooling air plenum.

Bundled tube fuel nozzle with internal cooling

A method for fabricating a main body of a trapped vortex fuel injector having a main body defining a fuel circuit. The method includes determining three-dimensional information of the main body including the fuel circuit where the fuel circuit is fully circumscribed within the main body and extends between an annular portion and a semi-annular portion of the main body and where the three-dimensional information of the main body further includes a plurality of fuel injection ports which provide for fluid communication between the fuel circuit and a trapped vortex pre-mix zone. The method further includes converting the three-dimensional information into a plurality of slices that define a cross-sectional layer of the main body and successively forming each layer of the main body by fusing a metallic powder using laser energy or electron beam energy.

Trapped vortex fuel injector and method for manufacture

A gas-only cartridge for a fuel nozzle includes a flange that defines a plurality of apertures for receiving a gaseous fuel, an outer tube that is coupled to the flange and an inner tube that extends axially within the outer tube. The inner tube and the outer tube define a fuel passage therebetween and the fuel passage is in fluid communication with the plurality of apertures of the flange. A fuel distribution tip is disposed at a downstream end of the gas-only cartridge and defines a plurality of fuel ports circumferentially spaced along and annularly arranged about an outer surface of the fuel distribution tip. The fuel ports are in fluid communication with the fuel passage.

Gas-only cartridge for a premix fuel nozzle

A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate to form an impingement air plenum therebetween. The combustor cap assembly further includes a flow conditioning plate coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion. The annular portion defines a plurality of flow conditioning passages. The inner band portion at least partially defines a cooling air plenum within the combustor cap assembly. The inner band portion defines an exhaust channel which is in fluid communication with the impingement air plenum and an exhaust outlet. The flow conditioning plate further defines a cooling air passage which provides for cooling air flow into the cooling air plenum.

Combustor cap assembly

A system includes a turbine combustor, which includes a first wall disposed about a combustion chamber, a second wall disposed about the first wall, and a third wall disposed about the second wall. The third wall is configured to combine an exhaust gas with an oxidant and the combustion chamber is configured to combust a mixture of a fuel, the oxidant, and the exhaust gas.

System and method for a multi-wall turbine combustor

A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor.

Fuel delivery system with moveably attached fuel tube

A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple mixing tubes. Each mixing tube includes an annular wall disposed about a central passage and an air inlet region configured to be disposed about a fuel injector extending into the central passage. The central passage extends from an upstream end to a downstream end of the annular wall relative to a direction of flow through the central passage. The air inlet region includes an air entry surface of the annular wall that gradually decreases in diameter in the direction of flow.

System and method for tube level air flow conditioning

A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple fuel injectors. Each fuel injector is configured to extend into a respective premixing tube of a plurality of mixing tubes. Each fuel injector includes a body, a fuel passage, and multiple fuel ports. The fuel passage is disposed within the body and extends in a longitudinal direction within a portion of the body. The multiple fuel ports are disposed along the portion of the body and coupled to the fuel passage. A space is disposed between the portion of the body with the fuel ports and the respective premixing tube.

System and method having multi-tube fuel nozzle with multiple fuel injectors

A combustor cap for a combustor chamber of a combustion system is provided. The combustor cap includes a plate member including: a plurality of openings for accommodating a plurality of fuel nozzles of the combustion system; a cooling passage extending through a plane of the plate member; an entrance opening to the cooling passage; and an exit opening from the cooling passage to a side of the plate member opposite to the combustion chamber.

Combustor cap with cooling passage

Embodiments of the present disclosure are directed to systems and methods for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of fuel injectors and a plurality of mixing tubes, wherein each mixing tube has a first portion for receiving one of the plurality of fuel injectors and a second portion having a mixing chamber that is configured to mix fuel and air. The length of the mixing chamber varies among the plurality of mixing tubes to allow for different mixing times.

Fuel-air mixing system with mixing chambers of various lengths for gas turbine system

Embodiments of the present disclosure are directed to a system having components for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of mixing tubes configured to receive and to mix fuel and air. Each mixing tube is paired with a fuel injector, and the fuel injector is positioned axially within a portion of the mixing tube. Fuel is injected from the fuel injector into the respective mixing tube, and air flows radially into each mixing tube through one or more apertures formed on the mixing tube. The fuel and air are mixed within the mixing tube and are deposited into a combustion chamber for combustion.

Multi-injector micromixing system

A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate.

Support frame and method for assembly of a combustion module of a gas turbine

A system includes a multi-tube fuel nozzle assembly. The multi-tube fuel nozzle assembly includes a support structure defining an interior volume configured to receive an air flow. The combustor cap assembly also includes multiple mixing tubes disposed within the interior volume. Each mixing tube of the multiple mixing tubes is configured to mix air and fuel to form an air-fuel mixture. The multi-tube fuel nozzle assembly further includes a combustor cap coupled to the support structure. The combustor cap includes multiple furcating nozzles integrated within the combustor cap. Each furcating nozzle of the multiple furcating nozzles is coupled to a respective mixing tube of the multiple mixing tubes. Also, each furcating nozzle of the multiple furcating nozzles is configured to receive a flow of the air-fuel mixture and to partition the flow of the air-fuel mixture into multiple air-fuel mixture flows.

A system for retaining a fuel nozzle premix tube includes a retention plate and a premix tube which extends downstream from an outlet of a premix passage defined along an aft side of a fuel plenum body. The premix tube includes an inlet end and a spring support feature which is disposed proximate to the inlet end. The premix tube extends through the retention plate. The spring retention feature is disposed between an aft side of the fuel plenum and the retention plate. The system further includes a spring which extends between the spring retention feature and the retention plate.

Fuel nozzle tube retention

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Horse Shoe, NC, United States of America

Patrick Benedict Melton