General Electric Company

Parker-hannifin Corporation

James Neil Cooper

Allen Michael Danis

Alfred Albert Mancini

Duane Douglas Thomsen

Michael Louis Vermeersch

Timothy James Held

Hukam Chand Mongia

Marie Ann McMasters

Steven Joseph Lohmueller

Gregory Allen Cimmarusti

Rex Jay Harvey

Mark David Durbin

Michael Philip Hagle

Daniel Lee Durstock

Douglas Marti Fortuna

Robert Thane Mains

Glenn Edward Wiehe

Peter Laing

Thomas Vander Ng

Michael Peter Wrubel

Barry Walford Savel

Junhaur Jih

Stephen W Falls

Byron Andrew Pritchard, Jr

James Thompson

John Michael Koshoffer

Robert Joseph Albers

James Michael Forrester

Jeffrey Michael Martini

Harjit Singh Hura

William Joseph Myers, Jr

Eric John Kress

Beverly Stephenson Duncan

Paul Edward Sabla

Hubert S Roberts, Jr

Stephen Eugene Melton

Joseph F Savelli

Shaun Michael DeVane

Mateusz Pawel Wenclik

John Lawrence Vandike

James N Reinhold, Jr

David B Legger

Erika Suzanne Show

Mary C Haas

William Joseph Myers Jr

Marek Krzysztof Krol

Timothy Glen Umbaugh

Doughal Marti Fortuna

Mark Durbin

Steven J Lohmueller

A method facilitates operating a gas turbine engine. The method comprises supplying steam to a nozzle, supplying primary fuel to the nozzle, discharging the steam into a combustor from a plurality of circumferentially-spaced steam outlets defined in a tip of the nozzle, and discharging the primary fuel into the combustor from at least one outlet that is spaced circumferentially between the steam outlets.

Methods and apparatus for injecting fluids into a turbine engine

A method for fabricating a gas turbine engine combustor that includes a domeplate and at least one fuel injector extending through an opening in the domeplate. The method includes fabricating a heatshield that includes a threaded collar extending upstream from the heatshield, positioning the heatshield on a downstream side of the domeplate such that the threaded collar is received within the domeplate opening, and coupling a retainer to the collar on an upstream side of the domeplate such that the domeplate is securely coupled between the heat shield and the retainer.

Method and apparatus for heat shielding gas turbine engines

A gas turbine engine fuel nozzle includes an axis of symmetry extending therethrough, the nozzle body including a first passage extending coaxially therethrough, a second passage, and a third passage, the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, and a nozzle tip coupled to the nozzle body, the nozzle tip including at least one primary discharge opening in flow communication with the first passage, at least one secondary discharge opening in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage.

Fuel nozzle for gas turbine engines

A method of operating a gas turbine engine is provided. The method includes discharging pilot fuel into a combustion chamber from a nozzle through at least one pilot fuel outlet defined in a tip of the nozzle, discharging steam from the nozzle through a plurality of steam outlets that are spaced circumferentially about the plurality of pilot fuel outlets, and discharging primary fuel from the nozzle through a plurality of primary fuel outlets that are circumferentially aligned with the plurality of steam outlets. To facilitate mixing the primary fuel with the steam, the primary fuel is discharged from the nozzle tip at an oblique angle with respect to a centerline extending through the nozzle tip.

A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled together, and coupling an outer support radially outward from the outer liner such that an outer passageway is defined between the outer liner and the outer support, wherein the outer support is configured to channel cooling air from the outer passageway towards at least a portion of the outer liner.

Method and apparatus for assembling gas turbine engine combustors

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; an outer cowl connected to the dome plate outer portion at a downstream end thereof; an inner cowl connected to the dome plate inner portion at a downstream end thereof; and, a deflector plate connected to and positioned aft of each opening in the dome plate. Each deflector plate further includes: an annular section at an upstream end thereof having a forward end, an aft end, an inner surface and an outer surface; a substantially planar flange connected to the aft end of the annular section, the planar flange including an outer circumferential surface, an inner circumferential surface, a first radial surface, a second radial surface, and an opening therein sized to the inner surface of the annular section so as to form opposing radial sections; a first flange connected to the outer circumferential surface of the planar flange at a predetermined angle thereto; and, a second flange connected to the inner circumferential surface of the planar flange at a predetermined angle thereto. The first and second radial sections of the deflector plate planar flange are configured so at least a portion of the dome plate cooling trough is in flow communication with a combustion chamber downstream of said dome plate.

Combustor dome assembly of a gas turbine engine having improved deflector plates

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between adjacent openings; an annular outer cowl connected to the outer portion of the dome plate; an annular inner cowl connected to the inner portion of the dome plate; and, a swirler located between the forward surface of the dome plate and the inner and outer cowls in substantial alignment with each of the openings in the dome plate. Each swirler further includes a forward portion and an aft portion and is retained by at least one tab member located upstream thereof so as to be movable in a radial and axial direction.

Combustor dome assembly of a gas turbine engine having a free floating swirler

A multi-staged gas turbine engine fuel supply system includes a plurality of fuel injectors and at least first and second staged fuel injection circuits in each of the fuel injectors. Each of the first and second staged fuel injection circuits includes first and second fuel injection points and at least first and second fuel nozzle valves operable to open at different first and second crack open pressures and controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector may have a valve housing with one of the first fuel nozzle valves and one of the second fuel nozzle valves contained therein.

Controlled pressure fuel nozzle system

A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

Method and apparatus to decrease combustor emissions

A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough includes: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings formed therein, wherein a radial section defined between each of the openings includes a cooling trough formed therein; and, a free floating swirler located upstream of the dome plate in substantial alignment with each of the openings in the dome plate, the swirler including a forward portion and an aft portion. The aft portion of each swirler is configured so as to permit air flow to the cooling trough during operation of the gas turbine engine. In particular, the swirler aft portion includes a substantially annular flange extending adjacent to the forward surface of the dome plate, wherein opposing portions of a circumference for the flange adjacent the radial sections of the dome plate are substantially linear.

Combustor dome assembly of a gas turbine engine having a contoured swirler

A multi-staged gas turbine engine fuel supply fuel injector includes at least first and second staged fuel injection circuits having first and second fuel injection points. At least first and second fuel nozzle valves operable to open at different first and second crack open pressures are controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector includes a valve housing containing the fuel nozzle valves.

Controlled pressure fuel nozzle injector

A gas turbine engine fuel injector conduit includes a single feed strip having a single bonded together pair of lengthwise extending plates. Each of the plates has a single row of widthwise spaced apart and lengthwise extending parallel grooves. Opposing grooves in each of the plates are aligned forming internal fuel flow passages through the strip from an inlet end to an outlet end. The feed strip includes a substantially straight middle portion between the inlet end and the outlet end. In one alternative, the middle portion has a radius of curvature greater than a length of the middle portion. The feed strip has at least one acute bend between the inlet end and the middle portion and a bend between the outlet end and the middle portion. The feed strip has fuel inlet holes in the inlet end connected to the internal fuel flow passages.

Fuel injector laminated fuel strip

A fuel injector nozzle for dispensing fuel in the combustion chamber of a gas turbine engine, includes an elongated, multi-layered, convoluted nozzle feed strip having an internal passage for directing fuel through the length of the strip from the inlet end to an outlet end; and a cylindrical, multi-layered fuel dispensing nozzle unitary with the feed strip and fluidly connected to the outlet end of the feed strip for dispensing the fuel. The multi-layered feed strip and nozzle allows complex porting of fuel circuits through the injector. The internal fluid passages through the feed strip and nozzle are formed by etching.

Multi-circuit, multi-injection point atomizer

A combustor liner has a stepped combustor liner surface and an overhang portion forming an air cooling slot. A contoured rear facing edge of the overhang portion reduces turbulence of combustion gas flow and reduces a combustor liner surface area exposed to combustion gases. A thermal barrier coating is also applied to the contoured rear facing edge, reducing heat flow into the overhang portion and hence reducing the operating temperature of the combustor liner. Thus, the amount of cooling air is reduced, which can reduce exhaust emissions increase engine performance and extend a working life of the combustor assembly.

Combustor rear facing step hot side contour method

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Hamilton, OH, United States of America

James Neil Cooper