General Electric Company

General Electric Technology Gmbh

David William Cihlar

Patrick Benedict Melton

Ronald James Chila

Christopher Paul Willis

Robert Joseph Rohrssen

Bradley Donald Crawley

William Lawrence Byrne

John Drake Vanselow

Lucas John Stoia

Wei A Chen

Abdul Rafey Khan

Christopher Paul Keener

Russell Pierson DeForest

Jun Cai

Matthew Paul Berkebile

Jonathan Glenn Reed

Andrew Grady Godfrey

Mert Enis Berkman

Jerome David Brown

Kevin Weston McMahan

Richard Martin DiCintio

William David York

Jason Thurman Stewart

Zhaoli Hu

Steven Charles Woods

Hasan Ul Karim

David Leach

Kassy Moy Hart

Timothy James Purcell

Donald Timothy Lemon

Jonathan Hale Kegley

Elizabeth Angelyn Fadde

Ajay Pratap Singh

Carolyn Ashley Crawley

David Philip Porzio

Marissa Ann Singley

Kassy Moy Lum

Benjamin Lamar Daniel

Kevin Woodlock

Kevin Weston Mcmahan

Russell Deforest

Patrick Bendict Melton

Willis Christopher Paul Paul

A process includes manufacturing a gas turbine fuel injector body having a stub flange extending radially outward about a circumference of the gas turbine fuel injector body. The stub flange is sized to engage a stepped ledge along a central opening of a mounting flange. The central opening is sized to receive the gas turbine fuel injector body. A gas turbine fuel injector includes a gas turbine fuel injector body and a mounting flange. A method of mounting a gas turbine fuel injector includes placing a stub flange of a gas turbine fuel injector body between a surface of an injector boss and a stepped ledge of a mounting flange. The method also includes securing the gas turbine fuel injector to the injector boss with a plurality of bolts, each bolt extending through a mounting hole in the mounting flange and into a threaded hole in the injector boss.

Gas turbine fuel injectors and processes

A staged injector in a combustor of a gas turbine. The staged injector may include an injector tube comprising a lateral wall enclosing an injection passageway that extends between an outlet and inlet. An outboard segment of the injector tube may include an exterior face. A cover may be formed about the outboard segment so form a surrounding plenum. The cover may include a side wall that radially overlaps the outboard segment and forms a first portion of the surrounding plenum therebetween. A ceiling wall of the cover may form a second portion of the surrounding plenum. A screening plate may be formed within the side wall of the cover that includes a multitude of apertures configured to fluidly connect the first portion of the surrounding plenum with a feed cavity formed exterior to the side wall.

Staged fuel and air injectors in combustion systems of gas turbines

A fuel injector assembly for a combustor including an axially staged fuel injector includes an injector body having an inner wall and a boss that is rigidly connected to the injector body the boss includes an inner wall. The inner wall of the boss and the inner wall of the injector body together define a flow passage of the fuel injector assembly. The injector body defines an inlet to the flow passage and the boss defines an outlet of the flow passage.

Combustor with axially staged fuel injector assembly

The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A bluff body extends radially between the flow sleeve and the liner through the cooling flow annulus. A guide vane is disposed within the cooling flow annulus and extends between the flow sleeve and the liner proximate to the bluff body.

Combustion liner cooling

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

An axial fuel staging (AFS) system for a combustor is provided. The AFS system includes a secondary fuel injector, an injector housing surrounding the secondary fuel injector, and a conduit assembly in flow communication with the secondary fuel injector. The conduit assembly includes a first conduit for conveying fuel to the secondary fuel injector, and a second conduit circumscribing the first conduit such that a channel is defined between the first conduit and the second conduit. The first conduit and the second conduit terminate within the injector housing.

Fuel supply conduit assemblies

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 sleeve assembly for a combustion system is provided. The sleeve assembly includes a liner defining a combustion chamber having a flow axis and a primary combustion zone. The liner has a forward end and an aft end such that the liner circumscribes the flow axis. The sleeve assembly also includes a shell circumscribing the liner such that a cooling duct is defined between the liner and the shell. The shell includes a unisleeve having a forward end and an aft end. The aft end of the unisleeve is positioned axially upstream of the aft end of the liner, defining a gap between the aft end of the liner and the aft end of the unisleeve. The unisleeve is mounted to the liner at circumferentially spaced locations along an axial plane between the forward end and the aft end of the unisleeve.

Sleeve assemblies and methods of fabricating same

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 bundled tube fuel nozzle includes a fuel distribution body. The fuel distribution body includes a substantially flat aft wall having an inner surface axially spaced from an outer surface, a fuel stem collar axially spaced from the inner surface of the aft wall and a contoured forward wall that extends between the fuel stem collar and the aft wall. The contoured forward wall and the aft wall define a fuel plenum within the fuel distribution body. The bundled tube fuel nozzle further includes a plurality of injector tubes that are in fluid communication with the fuel plenum. Each injector tube extends from the contoured forward wall to the aft wall within the fuel distribution body and defines a premix passage through the contoured forward, the fuel plenum and the aft wall.

Bundled tube fuel nozzle

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

An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion. A serpentine cooling passage is defined within the main body beneath the outer surface. The serpentine cooling passage is in fluid communication with the inlet port and the exhaust port. A conduit may be connected to the exhaust port for routing a compressed working fluid away from aft frame.

Internally cooled transition duct aft frame with serpentine cooling passage and conduit

A gas turbomachine nozzle includes a base portion having a first fluid inlet and a second fluid inlet, and an outlet portion having one or more outlets. A connection section fluidically connects the base portion and the outlet portion. An orifice plug is arranged in the base portion at the second fluid inlet. The orifice plug includes one or more openings fluidically connecting the second fluid inlet and the connection section.

Nozzle having an orifice plug for a gas turbomachine

A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow.

Combustion system having a venturi for reducing wakes in an airflow

An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough.

Aft frame and method for cooling aft frame

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Greenville, SC, United States of America

David William Cihlar