General Electric Company

Ge Avio S.r.l.

Joseph Douglas Monty

John Carl Jacobson

Stephen John Howell

Frank Anthony Lastrina

Kamil Bazyli Kaczorowski

Aureen Cyr Currin

Massimo Giovanni Giambra

David E Hrencecin

Narendra Digamber Joshi

Timothy Patrick McCaffrey

David Andrew Hannwacker

Shawn David Wehe

Owen James Sullivan Rickey

Changjin Yoon

Jacob S Hoffman

Thomas G Hill

Timothy P Mc Caffrey

ShihYang Hsieh

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 includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.

Gas turbine engine and combustor having air inlets and pilot burner

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

The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly comprises a volute walled enclosure defining a spiral scroll pitch axis disposed at least partially circumferentially around a centerline axis of the gas turbine engine, in which the walled enclosure is defined around the pitch axis, and the walled enclosure defines a combustion chamber therewithin.

Volute combustor for gas turbine engine

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 method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is aligned substantially concentrically with respect to a respective eyelet, coupling a baffle to each seal plate such that an opening defined in each baffle is aligned substantially concentrically with respect to a respective eyelet, and coupling a swirler assembly having an integrally formed swirler and flare cone to each seal plate such that the flare cone extends at least partially through the baffle opening, and such that cooling air may be directed towards the flare cone through openings formed in the assembly.

Methods and apparatus for fabricating gas turbine engine combustors

A gas turbine engine combustor fuel-air mixer includes a body having a substantially annular venturi and a longitudinal axis therethrough, an upstream end, a downstream end, and an inner surface. A primary radial jet swirler upstream of the venturi includes a plurality of radially extending primary air jets circumferentially and downstream angled with respect to the longitudinal axis. A plurality of axial jets axially extend through the primary swirler air and are circumferentially disposed around the longitudinal axis. An exemplary embodiment of the fuel-air mixer further includes the axial jets and the inner surface of a throat of the venturi being radially located at a radius from the longitudinal axis. The axial jets are located in an insert mounted to an upstream portion of the primary radial jet swirler and axially forward of the plurality of radially extending primary air jets. At least some of the axial jets have jet centerlines that intersect primary swirler centerlines of corresponding ones of the primary air jets downstream of outlets of the primary air jets.

Gas turbine engine combustor mixer

A combustor liner for use in a gas turbine engine includes an annular panel section having a cooling nugget formed on one end thereof. An annular cooling lip is formed on the cooling nugget so as to define a cooling slot. The cooling lip includes a hot side, a cold side and a trailing edge surface. The hot side defines a compound taper for minimizing the thickness of the trailing edge surface. In one embodiment, the compound taper includes a first tapered surface disposed on a forward portion of the cooling lip and a second tapered surface disposed on an aft portion of the cooling lip, wherein the second tapered surface has a greater taper than the first tapered surface.

Slot cooled combustor line

A combustor liner has a stepped combustor liner surface defining a combustion zone and an overhang portion forming an air cooling slot. A layer of thermal barrier material is applied to the combustor liner such that at least one portion of the combustor liner receives a layer of thermal barrier material with a thickness greater than 0.01 inches. Thus, the combustor liner absorbs less heat, and the combustor may operate at higher temperatures. As a result, low cycle fatigue and thermal creep are reduced within the combustor and the life cycle for the combustor is extended.

Methods for reducing heat load in combustor panels

Apparatus for reducing heat load in combustor panels

A combustor includes outer and inner liners joined at one end to an annular dome. A swirl cup is mounted to the dome and includes a flare cone extending therethrough. The flare cone has an obtuse flare angle for discharging fuel in a wide spray from an outlet of the cone. A flared beat shield surrounds the cone, and extends in part aft from the cone outlet, and is offset in part forwardly from the cone outlet to define a radially outwardly facing step.

Low emissions combustor

A combustor liner includes a row of primary dilution holes disposed aft of a forward end thereof, and a row of secondary dilution holes disposed between the primary holes and an aft end of the liner. The secondary holes vary in size circumferentially to a maximum size offset circumferentially from the primary holes.

Offset dilution combustor liner

A dome assembly for a single annular combustor of a gas turbine engine is disclosed as having a first dome wall in flow communication with compressed air supplied to the combustor, the first dome wall including a central opening therein and at least one cooling passage therethrough. A baffle is spaced downstream of and connected to the first dome wall at radially outward and inward ends, the baffle also including a central opening therein. A second dome wall defining the central opening in the first dome wall is provided which extends upstream of the first dome wall. A venturi is located within the central opening of the first dome wall, with the venturi including a flange extending radially outward from the central opening, wherein the second dome wall is connected to the flange at an upstream end. A flare cone is located within the central opening of the baffle and radially outward of the venturi, wherein a substantially radial passage is provided between the venturi flange and the flare cone, the radial passage having a swirler located therein. Accordingly, a chamber is formed by the first dome wall, the second dome wall, the baffle, the venturi, and the flare cone, the chamber being in flow communication with the compressed air entering the combustor by means of the cooling passage in the first dome wall, whereby the compressed air impinges on the baffle, circulates in the chamber, and exits through the swirler. In addition, a circumferential row of cooling passages is preferably located in the baffle adjacent the flare cone and rows of cooling passages are also located at both the radially outward and inward ends of the baffle.

Growing community of inventors

Boxford, MA, United States of America

Joseph Douglas Monty