General Electric Company

James Scott Flanagan

Jeffrey Scott LeBegue

Kevin Weston McMahan

Ronnie Ray Pentecost

Daniel Jackson Dillard

Jonathan Dwight Berry

Michael John Hughes

Patrick Benedict Melton

Stanley Kevin Widener

James Harold Westmoreland

Archie Lee Swanner, Jr

Ethan Conrad Schaeffer

Logan Tyler Nelson

Lewis Berkley Davis, Jr

Glen William Brooksby

Sandra Beverly Kolvick

Sarah Lori Crothers

Kaitlin Marie Graham

Thomas Alan Mogle, Ii

Joseph Vincent Citeno

Jaime Javier Maldonado

James Murray

James Joseph Murray, Iii

Travis Edwin Lipstein

Won-Wook Kim

Taylor Janae Million

Kevin Weston Mcmahan

Jeffrey Scott Lebegue

A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

Backwall strike braze repair

The present disclosure is directed to a fuel injection module for a segmented annular combustion system. The fuel injection module includes a housing body, a fuel nozzle portion, and at least one fuel injection lance. The fuel nozzle portion is fluidly coupled to a fuel nozzle plenum within the housing body, and the at least one fuel injection lance is fluidly coupled to an injector fuel plenum within the housing body. In some cases, the fuel nozzle portion is a bundled tube fuel nozzle having one or more subsets of tubes. The fuel injection lances are positioned along a radial side of the housing body or circumferentially between two subsets of tubes. Liquid fuel cartridges extend through the fuel nozzle portion, the fuel injection lances, or both.

Fuel injection module for segmented annular combustion system

A system for determining eccentricity of a turbine shell and a turbine rotor of a gas turbine includes a laser module with a microprocessor having coupled thereto a wireless network chip, a laser sensor, an inclination sensor, and a power supply. The laser sensor transmits a laser toward the turbine shell as the rotor spins at slow speed and to receive a reflected laser from the turbine shell, thereby defining a path length indicative of a distance between the laser module and the turbine shell for each of a series of points disposed circumferentially around the turbine shell. The system further includes a bracket configured to hold the laser module proximate to a turbine blade; a base station that produces a wireless network near the turbine shell and that receives distance measurements from the laser module for each of the series of points; and a server for processing the distance measurements into an eccentricity plot.

System and method for measuring eccentricity of turbine shell relative to turbine rotor

A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.

Segmented annular combustion system with dual fuel capability

A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustion system is part of a gas turbine.

Segmented annular combustion system with axial fuel staging

The present disclosure is directed to a bundled tube type fuel nozzle assembly. The fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band that extends between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the fuel plenum. Each tube of the plurality of tubes includes an inlet defined along an outer surface of the forward plate and an outlet defined downstream from the inlet. The forward plate defines a plurality of fuel inlet slots that is in fluid communication with the fuel plenum. Each fuel inlet slot extends radially outwardly with respect to an axial centerline of the fuel plenum body along the outer surface of the forward plate.

Fuel nozzle assembly with fuel inlet slots

A turbomachine includes a plurality of transition ducts and a support ring assembly. The outlet of a transition duct includes an inner flange and an outer flange. The turbomachine includes bore holes defined in the inner flange and outer flange, mating bore holes defined in the support ring assembly, and mechanical fasteners connecting the inner flange and the outer flange to the support ring assembly. A first one of the bore holes or mating bore holes has a first maximum radial gap and a first maximum tangential gap relative to an associated mechanical fastener. A second one of the bore holes or mating bore holes has a second maximum radial gap and a second maximum tangential gap relative to an associated mechanical fastener. The second maximum radial gap is greater than the first maximum radial gap or the second maximum tangential gap is greater than the first maximum tangential gap.

Transition duct assembly

A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each transition duct includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. Each transition duct further includes an upstream portion and a downstream portion. The turbomachine further includes a late injection assembly disposed between the upstream portion and the downstream portion of a transition duct and which provides fluid communication for an injection fluid to flow into the interior downstream of the inlet of the transition duct. The late injection assembly includes a late injection ring.

Transition duct assembly with late injection features

A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each of the plurality of transition ducts is offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly. The turbomachine includes a late injection assembly providing fluid communication for an injection fluid to flow into the interior downstream of the inlet of at least one transition duct of the plurality of transition ducts.

A turbomachine includes a plurality of transition ducts disposed in a generally annular array and including a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path, and a plurality of mechanical fasteners connecting at least one transition duct of the plurality of transition ducts to the support ring assembly.

A turbomachine includes a plurality of transition ducts disposed in a generally annular array. An outlet of each of the plurality of transition ducts is offset from an inlet along the longitudinal axis and the tangential axis. Each of the plurality of transition ducts further includes an upstream portion and a downstream portion, the upstream portion extending between the inlet and an aft end, the downstream portion extending between a head end and the outlet. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path. The turbomachine further includes a plurality of support assemblies directly connecting the upstream portion of at least one transition duct of the plurality of transition ducts to the support ring assembly. Each of the plurality of support assemblies includes a rod extending between the upstream portion and the support ring assembly.

A system with a gas turbine engine is provided. The gas turbine engine includes a first combustor comprising a first fuel nozzle, a second combustor comprising a second fuel nozzle, and a first fuel pressure oscillation system. The first fuel pressure oscillation system includes a first rotary device coupled to a first fuel circuit. The first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle. The first rotary device is configured to generate a first fuel pressure oscillation through the first fuel nozzle. The gas turbine engine also includes a second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit. The second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and the second rotary device is configured to generate a second fuel pressure oscillation through the second fuel nozzle.

Systems and methods for a fuel pressure oscillation device for reduction of coherence

A combustor includes an end cover having an outer side and an inner side, an outer barrel having a forward end that is adjacent to the inner side of the end cover and an aft end that is axially spaced from the forward end. An inner barrel is at least partially disposed concentrically within the outer barrel and is fixedly connected to the outer barrel. A fluid conduit extends downstream from the end cover. A first bundled tube fuel injector segment is disposed concentrically within the inner barrel. The bundled tube fuel injector segment includes a fuel plenum that is in fluid communication with the fluid conduit and a plurality of parallel tubes that extend axially through the fuel plenum. The bundled tube fuel injector segment is fixedly connected to the inner barrel.

System for supporting a bundled tube fuel injector within a combustor

A cap assembly for a bundled tube fuel injector includes an impingement plate and an aft plate that is disposed downstream from the impingement plate. The aft plate includes a forward side that is axially separated from an aft side. A tube passage extends through the impingement plate and the aft plate. A tube sleeve extends through the impingement plate within the tube passage towards the aft plate. The tube sleeve includes a flange at a forward end and an aft end that is axially separated from the forward end. A retention plate is positioned upstream from the impingement plate. A spring is disposed between the retention plate and the flange. The spring provides a force so as to maintain contact between at least a portion of the aft end of the tube sleeve and the forward side of the aft plate.

Growing community of inventors

Simpsonville, SC, United States of America

James Scott Flanagan