General Electric Company

Honeywell International Inc.

Haier US Appliance Solutions, Inc.

General Electric Technology Gmbh

Geoffrey David Myers

Thomas Edward Johnson

Kaitlin Marie Graham

Gregory Allen Boardman

Lewis Berkley Davis, Jr

Borys Shershnyov

Kevin Weston McMahan

Stephen Robert Thomas

Hua Zhang

Gilbert Otto Kraemer

Douglas Frank Beadie

Anthony Wayne Krull

Alexey Yurievich Gerasimov

Jonathan Dwight Berry

Willy Steve Ziminsky

Wei A Chen

Scott Robert Simmons

Krishna Kumar Venkataraman

Mark Allan Hadley

William Thomas Ross

Lucas John Stoia

Michael John Hughes

Timothy Andrew Healy

Hasan Ul Karim

Donald Mark Bailey

David Leach

Joseph Vincent Citeno

Nishant Govindbhai Parsania

Garth Curtis Frederick

Fabien Thibault Codron

Leonid Ginesin

Vijay Kumar Turaga

Natalya Igorevna Vyazemskaya

Kripa K Varanasi

David Martin Johnson

Stanley Kevin Widener

Seyed Gholamali Saddoughi

Kwanwoo Kim

Constantin Dinu

James Harold Westmoreland

David August Snider

Matthew Patrick Boespflug

Sam David Draper

Jun Cai

Alexey V Vert

Jeffrey Scott Goldmeer

Paul Burchell Glaser

Shiva Kumar Srinivasan

James Harper

Jayaprakash Natarajan

Almaz Kamilevich Valeev

Timothy Joseph Rehg

Nitin Bhate

Atul Kumar Vij

Mark William Pinson

Grover Andrew Bennett, Jr

John Thomas Herbon

William James Lawson

Ahmed Mostafa ELKady

Ram Srinivasan

Keegan Saunders O'Donnell

Daniel Robert Tegel

Leonid Yul'evich Ginesin

Shahryar Rabiei

Venkateswarlu Narra

Samer Aljabari

Stephen R Watts

Andrey Pavlovich Subbota

Xiaoguang Yu

Eric Motter

Jesse Blair Butler

Sergey Aleksandrovich Stryapunin

Jospeh Citeno

Stefan Maier

Joseph Zelina

Robert S Reynolds

Garth Frederick, Ii

Michael Draisey

Azardokht Hajiloo

Uyigue Omoma Idahosa

Borys Borysovych Shershnyov

Borys Borysovich Shershnyov

Alexey Vert

Anthony Krull

Mark Allen Hadley

A power generation system includes a combustion system, a liquid supply system, and a vapor supply system. The combustion system is configured to generate power by combusting an alternative fuel. The liquid supply system is configured to channel a liquid alternative fuel to the combustion system. The vapor supply system is configured to channel a vapor alternative fuel to the combustion system. The combustion system is ignited by combusting the liquid alternative fuel from the liquid supply system and is operated by combusting the vapor alternative fuel from the vapor supply system.

System and methods for igniting and operating a gas turbine engine with alternative fuels

A system includes a layered structure. The layered structure includes first and second coalesced layers and an intermediate layer disposed between the first and second coalesced layers. The first and second coalesced layers have a higher degree of coalescence than the intermediate layer.

System having layered structure and method of making the same

The present disclosure is directed to a fuel nozzle including a center body having a tube shape and a ring manifold disposed at an aft end of the center body. The fuel nozzle also includes an inner tube extending axially through the ring manifold and disposed within the center body. The inner tube is in fluid communication with a diluent supply. The fuel nozzle further includes a fuel tube extending helically around a portion of the inner tube. The fuel tube fluidly couples a fuel plenum of the ring manifold to a liquid fuel supply. Furthermore, the fuel nozzle includes a plurality of fuel injectors circumferentially spaced within an outer band of the ring manifold and in fluid communication with the fuel plenum. Each fuel injector is oriented to direct atomized liquid fuel radially outward from the center body. The ring manifold and the inner tube are thermally decoupled.

Dual-fuel fuel nozzle with gas and liquid fuel capability

An inlet manifold includes a main inlet oriented along a first direction and a pilot inlet oriented along a second direction perpendicular to the first direction. A wye passage includes an inlet branch in fluid communication with the main inlet. The inlet manifold also includes a first main passage in fluid communication with a first outlet branch of the wye passage and a second main passage in fluid communication with a second outlet branch of the wye passage. The first main passage extends generally along the first direction between the wye passage and a first main outlet. The second main passage extends generally along the first direction between the wye passage and a second main outlet. The inlet manifold also includes a pilot passage in fluid communication with the pilot inlet. The pilot passage extends generally along the first direction between the pilot inlet and a pilot outlet.

Fuel nozzle, fuel supply assembly thereof, and method of assembling a fuel nozzle

A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (), a number of radial fuel ports () in communication with the main fuel passage, a prefilmer surface () in communication with the radial fuel ports, and a main purge air passage () in communication with the radial fuel ports and the prefilmer surface.

Liquid fuel nozzles for dual fuel combustors

An annular fuel manifold includes an annular fuel plenum defined within the annular fuel manifold, an axial inlet into the annular fuel plenum, and a deflector downstream of the axial inlet, the deflector oriented such that fluid flow into the annular fuel plenum from the axial inlet is deflected by the deflector at least partially along a circumference of the annular fuel plenum.

Annular fuel manifold with a deflector

A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a premixing chamber formed between an outer annular shroud and an inner annular hub, a number of swirler vanes disposed about the premixing chamber between the outer annular shroud and the inner annular hub, one or more liquid fuel injectors positioned about the swirler vanes, and a flow of liquid fuel in communication with the one or more liquid fuel injectors.

Systems and methods for a multi-fuel premixing nozzle with integral liquid injectors/evaporators

A dual-fuel fuel nozzle includes a centerbody that at least partially defines an air plenum therein. A tip body is disposed at a downstream end of the centerbody. The tip body includes an upstream side that is axially spaced from a downstream side. The downstream side defines a circular slot and a circular recess that is positioned radially inwardly from the circular slot. The circular recess includes a floor and a side wall, The floor defines an insert opening and the side wall defines an annular groove that includes an undercut surface. The tip body further defines a plurality of orifices annularly arranged around the insert opening radially inward from the side wall of the circular recess. Each orifice includes an inlet that is in fluid communication with the air plenum and an outlet that is oriented towards the undercut surface.

Dual-fuel fuel nozzle with liquid fuel tip

The present disclosure is directed to a dual-fuel fuel nozzle that includes a center body having a tube shape and a gas fuel plenum defined within the center body. The duel-fuel fuel nozzle also includes a ring manifold defining a liquid fuel plenum disposed within the center body. The duel-fuel fuel nozzle further includes a plurality of radially oriented fuel injectors in fluid communication with the liquid fuel plenum. Additionally, the duel-fuel fuel nozzle includes an inner fuel tube extending axially within the center body. A portion of the inner fuel tube extends helically about an axial centerline of the center body. The inner fuel tube is in fluid communication with an axially oriented fuel injector. Furthermore, the duel-fuel fuel nozzle includes first fuel tube extending helically around a portion of the inner fuel tube within the center body. The first fuel tube is fluidly coupled to the fuel plenum.

A premixing fuel nozzle assembly for a turbomachine is disclosed as having at least one fuel injector with an outer jacket having a first end and a second end and a threaded surface disposed therebetween. The first end has a cylindrical sealing surface and the second end has at least one wrenching pocket. An annular hub is disclosed as having an aperture with a first end and a second end and a threaded surface disposed therebetween, wherein the aperture is configured to at least partially house the fuel injector therein and the annular hub further has a conical seat about the first end. The fuel injector cylindrical sealing surface swages inward to form a hermetic seal when contacting the annular hub conical seat as the fuel injector is threaded into the aperture.

Aerodynamic fastening of turbomachine fuel injectors

A system and method for igniting liquid fuel in a gas turbine combustor is provided. A liquid fuel cartridge, which is located within the head end, is in flow communication with a liquid fuel supply. A gaseous fuel nozzle is located proximate the liquid fuel cartridge and in flow communication with an auxiliary gaseous fuel supply. A controller is in communication with the liquid fuel supply, the auxiliary gaseous fuel supply, and an igniter located proximate or within the head end. The controller is configured to sequentially: initiate a gaseous fuel flow from the auxiliary gaseous fuel supply to the gaseous fuel nozzle; initiate the igniter to combust the gaseous fuel flow; initiate a liquid fuel flow from the liquid fuel supply to the liquid fuel cartridge; and terminate the gaseous fuel flow from the auxiliary gaseous fuel supply.

System and method for igniting liquid fuel in a gas turbine combustor

The present disclosure is directed to a dual-fuel fuel nozzle including a center body having a tube shape and a gas fuel plenum defined within the center body. The fuel nozzle also includes a plurality of turning vanes extending radially outward from the center body. Each turning vane includes at least one fuel port in fluid communication with the gas fuel plenum. A plurality of apertures is disposed through the plurality of turning vanes. The fuel nozzle further includes a ring manifold disposed within the center body downstream of the plurality of turning vanes. Additionally, the fuel nozzle includes a first fuel tube extending helically around a centerline of the center body. Furthermore, the fuel nozzle includes an air shield disposed within the center body and extending circumferentially around the first fuel tube.

Dual-fuel fuel nozzle with air shield

The present disclosure is directed to a nozzle assembly including a header manifold and a ring manifold, which defines a liquid fuel plenum, spaced from the header manifold. An outer sleeve connects to the ring manifold, and a nozzle body connects to the outer sleeve. The ring manifold, the outer sleeve, and the nozzle body define a fluid chamber. An inner fuel tube extends from the header manifold to the nozzle body. A portion of the inner fuel tube extends helically about an axial centerline of the nozzle assembly between the ring manifold and the nozzle body. A first fuel tube extends helically around a portion of the inner fuel tube. The first fuel tube fluidly couples the liquid fuel plenum to the header manifold. A second fuel tube extends helically around a portion of the inner fuel tube and fluidly couples the liquid fuel plenum to the header manifold.

Nozzle assembly for a dual-fuel fuel nozzle

A pre-film liquid fuel cartridge () includes a primary liquid fuel passage (), a plurality of inner fuel ports () and a plurality of outer fuel ports () that are in fluid communication with the primary liquid fuel passage. An inner pre-filming surface () is defined downstream from the plurality of inner fuel ports. The inner pre-filming surface () terminates at a first shear edge (). An outer pre-filming surface () is defined downstream from the plurality of outer fuel ports. The outer pre-filming surface () terminates at a second shear edge (). The first and second shear edges are relatively oriented so that a first pre-filmed liquid fuel sheet exiting the first shear edge intersects with a second pre-filmed liquid fuel sheet exiting the second shear edge, thereby atomizing the first and second pre-filmed liquid fuel sheets.

Pre-film liquid fuel cartridge

The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the primary fuel, a water passage, a number of secondary fuel injection ports, and a secondary fuel evaporator system for atomizing the secondary fuel.

Premixing nozzle with integral liquid evaporator

Growing community of inventors

Simpsonville, SC, United States of America

Geoffrey David Myers