General Electric Company

Brandon Taylor Overby

Patrick Benedict Melton

Lucas John Stoia

Richard Martin DiCintio

Keith Cletus Belsom

David Leach

Stuart Craig Hanson

Bryan Wesley Romig

Ronnie Ray Pentecost

Ibrahim Ucok

Jason Allen Seale

Jonathan Kay Allen

Kyle Eric Benson

Todd James Gattermeyer

Richard Martin Dicintio

A tool kit for decoupling a telescoping tube from a first liner of a gas turbine engine is disclosed. The tool kit includes a base plate coupled to a combustor casing. A post extends outward from the base plate into a combustion chamber defined by the liner. A plunger slidably mounts to the post and is slidable between an extended position and a retracted position. A lever arm pivotably couples to the post and the plunger. Pivoting the lever arm in a first direction slides the plunger to the extended position to decouple the telescoping tube from the liner. A retaining clip couples to the combustor casing and extends into an annular plenum at least partially defined between the liner and the combustor casing. The retaining clip defines a notch that receives the telescoping tube after the plunger assembly decouples the telescoping tube from the liner.

Tool kit and method for decoupling cross-fire tube assemblies in gas turbine engines

The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover. The fuel nozzle may include a pilot system in communication with the end cover passage.

Combustion casing manifold for high pressure air delivery to a fuel nozzle pilot system

A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as Oand Omixtures. The system also includes an aerodynamic peg disposed in the gas turbine combustor. The aerodynamic peg includes a first passage configured to convey a first fluid into the gas turbine combustor and a second passage configured to convey a second fluid into the gas turbine combustor. The first fluid and second fluid are different from one another.

System and method for fuel and steam injection within 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 turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage. The combustor casing includes an extruded fluid manifold mounted to the outer surface. The extruded fluid manifold includes first and second walls integrally formed with a third, connecting, wall. The first wall includes a first mounting element and the second wall includes a second mounting element. The first mounting element extends axially along the combustor casing away from the first wall and the second mounting element extends axially along the combustor casing away from the second wall and the first mounting element. The extruded fluid manifold is joined to the outer surface of the combustor casing through the first and second mounting elements.

Extruded fluid manifold for gas turbomachine combustor casing

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Spartanburg, SC, United States of America

Brandon Taylor Overby