General Electric Company

Ge Avio S.r.l.

Stephen John Howell

John Carl Jacobson

Barry Francis Barnes

Timothy Patrick McCaffrey

David Andrew Hannwacker

Joseph Douglas Monty

Jennifer Waslo

Robert Gregory Carita

Massimo Giovanni Giambra

Allen Michael Danis

Elias Harry Lampes

Ramy Michael Souri

Walter Jackson Tingle

Steven M Toborg

Joseph D Cohen

John W Vinson

Thet Kwan

Jennifer Caiulo

Grant A Albert

Timothy P Mccaffrey

Thet Don Kwan

An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

Reverse flow combustor

A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surface and an outer surface and a first plurality of cooling channels defined between the inner and outer surfaces. The combustor assembly also includes a sleeve substantially circumscribing the combustor liner such that an annular cavity is defined between the combustor liner and the sleeve. The sleeve includes a second plurality of cooling channels defined therethrough that are configured to channel a fluid against the combustor liner outer surface.

Combustor assemblies for use in turbine engines and methods of assembling same

A combustor assembly for a gas turbine engine includes an inner liner, an outer liner, and a combustor dome. The inner liner, outer liner, and combustor dome together define at least in part a combustion chamber having an annulus height. Additionally, the combustor assembly includes a fuel-air injector hardware assembly positioned at least partially within an opening of the combustor dome. The fuel-air injector hardware assembly includes a heat shield located at least partially within the combustion chamber, the heat shield defining an outer diameter. A ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield may be at least about 1.5:1.

Combustor assembly

A combustor assembly for a gas turbine engine includes a combustor dome defining an opening, a cooling hole, and at least in part defining a combustion chamber. The combustor dome includes a first side and a second side, the cooling hole extending from the first side to the second side. The combustor assembly additionally includes a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and including a heat shield. The heat shield includes a heat deflector lip. The cooling hole in the combustor dome is oriented to direct a cooling airflow onto the heat deflector lip to maintain at least a portion of the heat shield within a desired operating temperature range.

A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner formed integrally of a ceramic matrix composite material. The combustor dome defines a plurality of openings for receiving a respective plurality of fuel air injector hardware assemblies and may extend continuously along a circumferential direction.

A combustor assembly for a gas turbine engine includes a combustor dome and a combustion chamber liner attached to or formed integrally with the combustor dome. The combustion chamber liner extends between a forward end and an aft end, and together with the combustor dome at least partially defines a combustion chamber. The combustor assembly additionally includes a mounting assembly attached to the liner proximate the forward end of the liner for supporting the combustor dome and combustion chamber liner within the gas turbine engine relative to a structural component of the gas turbine engine.

A combustor assembly for a gas turbine engine includes a combustor dome having a hot side and a cold side and at least in part defining a combustion chamber. The combustor assembly additionally includes a fuel-air injector hardware assembly having a first member and a second member. The first member is positioned at least partially adjacent to the cold side of the combustor dome and the second member is positioned at least partially adjacent to the hot side of the combustor dome. The first and second members together define an attachment interface joining the first member to the second member and mounting the fuel-air injector hardware assembly to the combustor dome. The attachment interface may be shielded from the combustion chamber to protect the attachment interface from an undesirable amount of thermal expansion and to maintain the materials within desired material operating temperature limits.

A combustor assembly includes a first combustion chamber member and a second combustion chamber member. The first and second combustion chamber members are each formed of a CMC material and include adjacently positioned coupling flanges. A mounting assembly includes a pair of mounting flanges positioned on opposite sides of the coupling flanges of first and second combustion chamber members. An attachment member of the mounting assembly clamps the pair of mounting flanges together to mount the first and second combustion chamber members.

A combustor assembly for a gas turbine engine is includes a liner and a combustor dome formed of a ceramic matrix composite material. The combustor dome and liner together define at least in part a combustion chamber. The combustor dome extends along a circumferential direction and defines one or more openings, the combustor dome is configured to receive one or more fuel-air injector hardware assemblies in or through the one or more openings.

A combustor assembly for a gas turbine engine includes a liner and a combustor dome. The combustor dome and liner together at least in part define a combustion chamber. The combustor dome includes a transition portion and a forward wall. The transition portion extends from the forward wall towards the liner. Additionally the transition portion may define an angle relative to the forward wall and/or may define a radius of curvature between the forward wall of the combustor dome and a flat of the transition portion of the combustor dome for increasing an aerodynamic efficiency of the combustor dome.

Combustor assembly for a gas turbine engine

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.

Growing community of inventors

West Newbury, MA, United States of America

Stephen John Howell