General Electric Company

Ge Infrastructure Technology, LLC

Keith Cletus Belsom

Lucas John Stoia

Jonathan Dwight Berry

Patrick Benedict Melton

Donald Timothy Lemon

Clay Thomas Griffis

Larry Lou Thomas

Kevin Weston McMahan

Thomas James Batzinger

Paul Stephen DiMascio

Richard Martin DiCintio

Ronald James Chila

Heath Michael Ostebee

Abdul-Azeez Mohammed-Fakir

James Harold Westmoreland

Ronnie Ray Pentecost

Charles Van Buchan

Charles E Steber

Bradley Donald Crawley

Almaz Kamilevich Valeev

Bruce J Badding

Richard Lee Nichols

Calvin Levy Sims

Seth Reynolds Hoffman

Alberto Jose Negroni

Thomas Earnest Moldenhauer

Brandon Taylor Overby

Natesh Chandrashekar

Matthew Eugene Roberts

Daniel Robert Tegel

Jonathan Kay Allen

John M Matthews

Kyle Eric Benson

Tiffany M Craig

Henry Joe Wiersma

Jesse Barton

John Alfred Simo

David Kevin Spikings

Michael Damian Seal

Marshalla Michelle Wright

Mark Steadman

Martin Brown

Arunkant Ramdas Bhat

Sarah Jane Hutcherson

Thomas Charles Almond, Iii

Kevin Weston Mcmahan

Richard Martin Dicintio

Bruce John Badding

The present application provides a cooling hole location system for locating a cooling hole in a gas turbine component, wherein the cooling hole is covered by a thermal barrier coating. The cooling hole location system may include a light source positioned on a first side of the gas turbine component and an optical detector positioned on a second side of the gas turbine component. The optical detector detects light from the light source visible through the thermal barrier coating covering the cooling hole.

Systems and methods of locating cooling features in a gas turbine component under thermal barrier coatings

The present application provides an aft plate removal tool for servicing a combustor. The combustor includes an aft plate with a central passage and a number of tubes extending through the aft plate. The aft plate removal tool includes a central screw, a lower housing attached to the central screw, the lower housing including a number of spring loaded lower housing feet, and an upper housing attached to the center screw, the upper housing including a number of spring loaded upper housing feet. The aft plate removal tool is inserted through the central passage of the aft plate such that rotation of the upper housing advances the spring loaded upper housing feet against the aft plate until the spring loaded upper housing feet push the aft plate off of the tubes.

Aft inner cap plate removal method and tooling for a combustor with micromixer tubes

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

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

A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas turbine and the plurality of turbine combustors. The first seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors. The gas turbine engine also includes a second seal disposed between the gas turbine and the plurality of turbine combustors. The second seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors.

System for sealing between combustors and turbine of gas turbine engine

A corrosion sensor for an internal structure of a machine is provided. The corrosion sensor may include a test cap having at least one of a material and a geometry configured to fail faster than a material of the internal structure due to a corrosive influence. A mount secures the test cap in position in an opening in a portion of the machine that defines an operational environment. A chamber is adjacent the test cap and in at least one of the test cap and the mount. A failure in the test cap creates an environmental change in the chamber that indicates exceeding a corrosion threshold and can be sensed by, for example, a temperature or pressure change.

Corrosion sensor for internal structure of machine

A combustor () includes a cap (), a liner (), a transition piece (), and a combustion chamber () located downstream from the cap () and defined by the cap and liner. A secondary nozzle () circumferentially arranged around the liner () or transition piece () includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding the center body, and an annular passage between the center body and the shroud. A method for supplying fuel to a combustor () includes flowing fuel through a primary nozzle radially disposed in a breech end of the combustor and flowing fuel through a secondary nozzle () circumferentially arranged around and passing through at least one of a liner () or a transition piece. The secondary nozzle () includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body (), and an annular passage between the center body and the shroud.

Combustor and method for supplying fuel to a combustor

A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.

Crossfire tube assembly with tube bias between adjacent combustors

A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.

Fuel nozzle for a combustor of a gas turbine engine

A combustor includes an upstream surface that extends radially across at least a portion of the combustor, a downstream surface that extends radially across at least a portion of the combustor and is axially separated from the upstream surface, and a plurality of tubes that extend through the downstream surface. A resonator is upstream from at least one of the tubes, and a fluid passage extends through the resonator and into the least one tube.

Combustor

A device for supplying flow across a combustor includes an axial fluid injector configured to circumferentially surround at least a portion of the combustor. An inner annular passage extends through the axial fluid injector and provides fluid communication through the axial fluid injector and into a first annular passage that surrounds the combustor. An outer annular passage extends through the axial fluid injector radially outward from the inner annular passage and provides axial flow into the first annular passage. A method for supplying flow to a combustor includes flowing a first portion of a working fluid through a first axial flow path and flowing a second portion of the working fluid through a second axial flow path.

Combustor and method for supplying flow to a combustor

A combustor casing fuel injector in a combustor of a combustion turbine engine, the combustor including a combustor casing that encloses internal structure of the combustor, wherein the combustor casing fuel injector includes a fuel manifold adjacent to an outer surface of the combustor casing. In certain embodiments, the combustor casing fuel injector includes a fuel injector; wherein the fuel injector extends through the combustor casing from a position within the fuel manifold to a predetermined fuel injection location; and wherein the fuel injector includes a protruding injector inlet within the fuel manifold.

Apparatus and systems relating to fuel injectors and fuel passages in gas turbine engines

A fuel nozzle for a gas turbine includes a fuel nozzle body or endcover. The fuel nozzle body or endcover includes at least one seal surface. The fuel nozzle also includes at least one flexible hose and at least one flange connected to the flexible hose. The at least one flange is fastened to the fuel nozzle body at the at least one seal surface.

Integral flange connection fuel nozzle body for gas turbine

A system for assembling an end cover of a combustor includes a connector and structure for engaging the connector to an insert positioned at least partially inside the end cover. The system also includes structure for moving the connector axially with respect to the end cover. A method for assembling an end cover of a combustor includes inserting a connector through at least a portion of the end cover and an insert positioned at least partially inside the end cover. The method further includes engaging the connector with the insert and moving the connector axially with respect to the end cover to compress the insert against the end cover.

System and method for assembling an end cover of a combustor

Growing community of inventors

Laurens, SC, United States of America

Keith Cletus Belsom