Honeywell International Inc.

Uop Lcc

Rodolphe Dudebout

Frank Joseph Zupanc

Nagaraja S Rudrapatna

Paul Yankowich

Atul Verma

Sunil James

Gregory O Woodcock

Jurgen C Schumacher

Terrel Kuhn

Gavin Paul Towler

Robert L Bedard

Laura Elise Leonard

Christopher Naunheimer

Donald L Mittendorf

David Chou

Christopher Zollars

Mario Scaini

Hamdullah Ozogul

Terrel E Kuhn

Mark C Morris

Ardeshir Riahi

David R Waldman

Aziz A Sattar

Eric Blumer

Michael T Barton

Shakeel Nasir

Vinayender Kuchana

Raymond Gage

Thomas J Bronson

William J Howe

Christopher David Gatto

James Neumann

Robert Saunders Murray

Ronald B Pardington

Lowell Frye

Victor Reyes

David H Edmonds

Douglas P Freiberg

Jeffrey Krise

John Gintert

Michael Ryan Wedig

Craig W McKeever

Art Payne

Sossity A Flamand

Roger J DeRudder

Amy Kujala

Ryan Meyer

Bradley Culbertson

Richard J Musiol

Duane Peterson

Dustin Brandt

Richard R Bohman

Doni Tapederi

Jacob Salai

Jaydeep Basani

Girish Kanakagiri

Venkatesha Prasad

Veeraraghava Raju Hasti

Veeraraghave Raju Hasti

Paul Yankowitch

Michael Wedig

Tony J Keeton

Victor M Reyes

Paul R Yankowich

Frank J Zupanc

A gaseous fuel nozzle includes a main body, a plurality of inner air injection passages having inlet and outlet ports, a plurality of outer air injection passages having inlet and outlet ports, and a plurality of gaseous fuel injection passages having inlet and outlet ports. At least the gaseous fuel injection outlet ports are disposed concentrically about an axis of symmetry and between the plurality of inner air injection nozzle outlet ports and the plurality of outer air injection nozzle outlet ports.

Gaseous fuel nozzle for use in gas turbine engines

A system and method for supplying hydrogen to a combustor of a gas turbine engine includes supplying liquid hydrogen from a liquid hydrogen supply source to a hydrogen supply line that is adapted to be coupled to the combustor of the gas turbine engine. The liquid hydrogen is converted to gaseous hydrogen at a first pressure and is to a pump, which increases the pressure of the gaseous hydrogen to a second pressure. A flowrate of the gaseous hydrogen discharged from the pump is controlled using a fuel metering valve. A portion of the gaseous hydrogen discharged from the pump is received and stored in a high-pressure gaseous hydrogen tank, and a pressure-regulating valve maintains the second pressure at a substantially constant pressure magnitude.

Gas turbine engine hydrogen supply system and method

An injector module includes an injector stem that extends along an injector longitudinal axis between an inlet end and an outlet end of the injector module. The injector module also includes a first fuel line of a first fuel circuit at least partly extending through the injector stem. The first fuel line has a first outlet disposed at the outlet end of the injector stem. The injector module further includes a second fuel line of a second fuel circuit at least partly extending through the injector stem. The second fuel line has a second outlet disposed at the outlet end of the injector stem. The first outlet and the second outlet are spaced apart and have different orientations relative to the injector longitudinal axis. The first fuel line is thermally coupled to the second fuel line.

Gas turbine engine injector module with thermally coupled fuel lines having respective outlets

A deswirl system for a gas turbine engine includes a deswirl shroud, and at least one deswirl vane having a leading end and a trailing end. The deswirl system includes a deswirl hub spaced apart from the deswirl shroud by the at least one deswirl vane. The deswirl hub includes a hub body that extends at a first angle and a hub extension that extends beyond the trailing end of the at least one deswirl vane. The hub extension extends from the hub body at a second angle, and the first angle is different than the second angle.

Deswirl system for gas turbine engine

A coating occlusion resistant effusion cooling hole to form a film of a cooling fluid on a surface of a wall. The cooling hole extends along a longitudinal axis. The cooling hole includes an inlet section defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section fluidly coupled downstream of the metering section. The outlet section includes an overhang portion, a recessed portion, a first sidewall and a second sidewall. The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.

Coating occlusion resistant effusion cooling holes for gas turbine engine

A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.

Combustor for gas turbine engine and method of manufacture

A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.

Plug resistant effusion holes for gas turbine engine

An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.

A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.

Axially staged rich quench lean combustion system

A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.

A gas turbine engine component includes a hot side surface that is configured for exposure to a hot gas flow path, a second surface that is opposite the hot side surface and not exposed to the hot gas flow path, and an effusion cooling aperture positioned along the hot side surface. The effusion cooling aperture includes a recessed portion including a void area beginning at the hot side surface and extending inwardly therefrom, a forward surface, an entirety of which is angled at 90 degrees or greater than 90 degrees with respect to the hot side surface, defining a forward end of the recessed portion, an inward surface, angled with respect to the hot side surface, and connecting the forward surface to the hot side surface, and an overhang portion connected with the hot side surface and extending aftward from the forward surface and over the void area.

Gas turbine engine components with air-cooling features, and related methods of manufacturing the same

A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

Gas turbine engine dual-wall hot section structure

Apparatus and methods are provided for converting methane in a feed stream to acetylene. A hydrocarbon stream is introduced into a supersonic reactor and pyrolyzed to convert at least a portion of the methane to acetylene. The reactor effluent stream may be treated to convert acetylene to another hydrocarbon process.

Methane conversion apparatus and process using a supersonic flow reactor

A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.

Gas turbine engines with plug resistant effusion cooling holes

Growing community of inventors

Phoenix, AZ, United States of America

Rodolphe Dudebout