General Electric Company

Barry Francis Barnes

Stephen John Howell

John Carl Jacobson

Timothy Patrick McCaffrey

Ramy Michael Souri

Walter Jackson Tingle

Thet Kwan

Timothy P Mccaffrey

Thet Don Kwan

A method facilitates assembling a combustor for a gas turbine engine, wherein the combustor includes a swirler assembly. The method comprises machining material to form a domeplate, positioning a sealplate including an overhanging portion against the domeplate, securing the sealplate in position relative to the domeplate with a welding process, and welding the swirler assembly to the domeplate.

Methods for assembling gas turbine engine combustors

A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor, coupling a ring support that includes a first radial flange, a second radial flange, and a plurality of beams that extend therebetween to the combustor casing, and coupling a primer nozzle including an injection tip to the combustor such that the primer nozzle extends axially through the dome assembly such that fuel may be discharged from the primer nozzle into the combustor during engine start-up operating conditions.

Methods and apparatus for operating gas turbine engine combustors

Methods and apparatus for attaching swirlers to gas turbine engine combustors

An ignition device assembly for a gas turbine engine combustor includes a body and a shroud. The body extends from an inlet end to an outlet end, and the shroud extends circumferentially around at least a portion of the body, and axially from a first end to a tip end. The shroud includes a tip portion and a body portion. The body portion includes a plurality of metering openings and a plurality of first outlet openings. The plurality of metering openings are for channeling cooling air to the ignition device body, and the plurality of first outlet openings are for channeling spent cooling air from the ignition device body. The tip portion includes a plurality of discharge openings extending therethrough for channeling cooling from the ignition device body. The plurality of first outlet openings are between the shroud tip portion and the plurality of shroud metering openings.

Methods and apparatus for cooling turbine engine combustor ignition devices

A combustor includes an outer wall and an inner liner joined to an inner shell in turn mounted to an inner casing. The casing includes a first rabbet at an end flange in which is mounted a corresponding flange of the inner shell. The inner shell also includes a second rabbet which receives an end flange of the inner liner. The inner shell is trapped in the first rabbet by an inner retainer. And, the inner liner is trapped in the surrounding second rabbet for aft-mounting the liner and shell to the inner casing.

Rabbet mounted combuster

An outer combustor wall () includes an outer support shell () surrounding an outer combustion liner (). The shell () includes a first radial aft flange (), and the liner () includes a second radial aft flange () axially adjoining the first flange. An annular retainer () and seal () are joined to the first flange for slidingly trapping the second flange therebetween for thermally floating the liner on the shell.

Floating liner combustor

A method facilitates assembling a combustor for a gas turbine engine. The method includes providing a dome assembly that includes at least one cooling slot lip and at least one filler projection, wherein a gap defined between the cooling slot lip and the at least one filler projection has a height defined between cooling slot lip and the at least one filler projection that is substantially uniform through the gap. The method also includes coupling a liner assembly to the dome assembly, such that a combustion chamber is defined by the liner assembly, and coupling an inner and an outer support to the dome assembly, such that the dome assembly extends between the inner and outer supports.

Methods and apparatus for film cooling gas turbine engine combustors

A combustor includes outer and inner liners joined together by a dome to define a combustion chamber. A row of air swirlers is mounted in the dome and includes corresponding main fuel injectors for producing corresponding fuel and air mixtures. Pilot fuel injectors fewer in number than the main injectors are mounted in the dome between corresponding ones of the swirlers. Staged fuel injection from the pilot and main injectors is used for starting the combustor during operation.

Sector staging combustor

A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor, coupling a fuel injector including a fuel inlet and an air inlet to the combustor casing such that the fuel injector extends axially through the dome assembly such that fuel may be discharged from the primer nozzle into the combustor, and coupling the air inlet to an air source such that cooling air received therethrough is circulated through the fuel injector to facilitate cooling the fuel injector.

A combustor baffle includes an annular splashplate having a center mounting tube therein for receiving a carbureted stream. A semi-ferrule is offset both laterally and transversely from the tube, and is open laterally outwardly therefrom. The semi-ferrule cooperates with an adjoining semi-ferrule for defining a port in which a pilot injector or igniter may be mounted.

Growing community of inventors

Malden, MA, United States of America

Barry Francis Barnes