General Electric Company

Ge Infrastructure Technology, LLC

Ge Vernova Infrastructure Technology LLC

Other

General Electric Technology Gmbh

Michael John Hughes

Jonathan Dwight Berry

Stanley Kevin Widener

Gregory Allen Boardman

James Scott Flanagan

Johnie Franklin McConnaughhay

Willy Steve Ziminsky

Kevin Weston McMahan

Jason Thurman Stewart

Bradley Donald Crawley

Thomas Edward Johnson

Geoffrey David Myers

William David York

Joseph Vincent Citeno

Chunyang Wu

Wei Zhao

Kara Johnston Edwards

Srikanth Chandrudu Kottilingam

Matthew Troy Hafner

Victor John Morgan

Neelesh Nandkumar Sarawate

Deepak Trivedi

Ronald James Chila

Abdul Rafey Khan

Fei Han

William Forrester Seely

Jong Ho Uhm

Hasan Ul Karim

Derrick Walter Simons

Bryan Wesley Romig

Ibrahim Sezer

Russell Pierson DeForest

Juergen Gerhard Hoffmann

Jayaprakash Natarajan

Almaz Kamilevich Valeev

Atul Kumar Vij

Majed Sammak

Nicholas Magina

Homayoon Feiz

Sreenivasa Rao Gubba

Hatem M Selim

Abdurrahman Abdallah Khalidi

Alaaeldin Elsaeed Dawood

Baha Suleiman

Timothy Healy

Krishna Kant Agarwal

Rajani Kumar Akula

Carlo Antonio Arguinzoni

Azardokht Hajiloo

Heath Michael Ostebee

Carlos Miranda

Kevin Weston Mcmahan

Jonathan Dwight Bery

Fuel injection assemblies and combustors are provided. The fuel injection assembly includes a fuel injector that is configured to couple to an outer sleeve of the combustor. The fuel injection assembly further comprises a boss that is spaced apart from the fuel injector and is configured to couple to a combustion liner of the combustor. The boss includes a flange portion, an annular wall portion extending from the flange portion, and an interior surface. The boss defines a serpentine cooling passage that extends from an inlet on the flange portion to an outlet on the interior surface.

Fuel injection assembly having a boss with a serpentine cooling passage

Combustors and methods of operation are provided. The combustor includes a combustion liner that defines a combustion chamber and that extends along an axial centerline from a forward end to an aft end. The combustor further includes a center fuel nozzle that extends along the axial centerline at least partially within the combustion chamber. The combustor further includes a plurality of outer fuel nozzles that surround the center fuel nozzle. The plurality of outer fuel nozzles terminates at the forward end. A venturi injector is positioned in the combustor within the combustion chamber downstream of the center fuel nozzle. The combustor further includes an injector that is coupled to the combustion liner and downstream of the venturi injector.

Flex fuel combustor

A gas turbine combustion system includes a combustor that has at least two injection stages each configured to inject fuel into a combustion chamber of the combustor. A fuel supply circuit is in fluid communication with the at least two injection stages for providing the fuel from a fuel supply to the injection stages. The fuel supply circuit includes at least two branches, each branch being fluidly coupled to a respective injection stage. The gas turbine combustion system further includes at least two heat exchangers fluidly coupled to a thermal fluid supply. Each heat exchanger is disposed in thermal communication on a respective branch of the at least two branches for modifying a temperature of fuel within the respective branch.

Fuel supply system for a combustor

A method of operating a gas turbine combustor includes: selectively directing fuel and a first air supply through a fuel nozzle assembly in a head end section to produce a first fuel/air mixture, which is ignited within a liner to produce combustion gases; selectively directing a second fuel/air mixture through the liner from at least one first injector disposed at a first axial location; selectively directing a third fuel/air mixture through the liner from at least one second injector disposed at a downstream, second axial location. Each of the fuel nozzle assembly, the first injector(s), and the second injector(s) receives only a respective air supply from a compressor discharge plenum. The second injector(s) receive a respective air supply that is greater than each of the respective air supplies of the fuel nozzle assembly and the first injector(s).

Method of operating gas turbine combustor with multiple fuel stages

An axial fuel stage (AFS) injector includes a mixing member and a high pressure (HP) air-fuel injection member. The injection member includes HP air-fuel injectors including an inner wall defining an inner air jet and an outer wall surrounding and concentric with the inner wall and defining an outer air jet loop therebetween. A spacer member spaces the walls. A plurality of fuel injector passages extends from the outer wall through the spacer member and the inner wall to the inner air jet. Each fuel injector passage has an end including a fuel injector directed into the inner air jet. A fuel plenum is configured to deliver a fuel to each of the fuel injectors. The inner air jets and the air jet loops are configured to direct a high-pressure air flow from a high-pressure air source with the fuel into the inlet of the mixing member.

Axial fuel stage injector creating air curtain

A bundled tube fuel nozzle assembly for a gas turbine combustor includes: a forward plate facing a head end air plenum, an aft plate facing a combustion chamber, and premixing tubes extending from the forward plate to the aft plate. An interior side wall extends circumferentially around the first plurality of premixing tubes and defines an interior fuel plenum, and an exterior side wall extends circumferentially around the interior side wall and defines an exterior fuel plenum. Both side walls extend axially from the forward plate to the aft plate. The interior fuel plenum is in fluid communication with the exterior fuel plenum. Each premixing tube includes at least one fuel injection hole therethrough, which is in fluid communication with the interior fuel plenum. The head end air plenum is in fluid communication with the combustion chamber, via inlet ends of the premixing tubes.

Bundled tube fuel nozzle assembly for gas turbine combustor

A method includes delivering fuel and a first portion of oxidant as a rich mixture to the first zone of the combustion chamber. The fuel includes ammonia (NH). The method further includes burning the rich mixture in the first zone. Combustion gases containing nitrogen oxides (NOx) are produced. The method further includes delivering a second portion of oxidant into the second zone to break down unburned ammonia into ammonia intermediates in the second zone. The nitrogen oxides (NOx) are consumed by reacting with the ammonia intermediates in the second zone. Byproduct hydrogen is produced as a result of breaking down the unburned ammonia into the ammonia intermediates. The method further includes delivering a third portion of oxidant into the third zone. The byproduct hydrogen is burned in the third zone. The third portion of oxidant is greater than the first portion of oxidant and the second portion of oxidant.

Ammonia fired combustor operating method

Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a boss that forms at least a portion of an annular wall. The annular wall defines a mixing channel that extends along a center axis. The fuel injection assembly further includes a fuel injector that has a radially outer wall and a radially inner wall that at least partially defines a fuel plenum. The fuel injector further includes a plurality of premix tubes that each extend along an injection axis from an inlet end on the radially outer wall through the fuel plenum to an outlet end, and wherein the injection axis is slanted towards the center axis of the mixing channel.

Fuel injection assembly for a combustor

A method for detecting flameholding in at least one combustor of a turbine engine includes measuring dynamic pressure data of the at least one combustor of the turbine engine; converting the dynamic pressure data to frequency-domain spectral energy amplitudes for the dynamic pressure data; and comparing the spectral energy amplitudes against a dynamic amplitude threshold value to determine whether the amplitudes exceed the threshold minimum amplitude value, wherein exceeding the dynamic amplitude threshold indicates a flameholding occurrence.

Methods and systems to detect flameholding in turbine assemblies

A method of operating a combustor of a turbomachine on a total fuel input that contains a concentration of hydrogen that is greater than about 80% is provided. The method includes injecting a first mixture of air and a first fuel containing a first amount of hydrogen into the primary combustion zone of the combustor to generate a first flow of combustion gases having a first temperature. The method further includes injecting, with one or more premix injectors disposed downstream of the fuel nozzles, a second mixture of air and a second fuel containing a second amount of hydrogen into the secondary combustion zone of the combustor to generate a second flow of combustion gases having a second temperature. The method further includes separately injecting a third fuel into secondary combustion zone to generate a third flow of combustion gases having a third temperature.

Methods of operating a turbomachine combustor on hydrogen

An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment, the combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The combustion liner defines a cavity forward of the turbine nozzle. The cavity extends between the first side wall and the second side wall. An impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members configured to direct coolant to impinge upon the first side wall and the second side wall. Each impingement member extends from a respective inlet defined within the flange to a respective closed end. A plurality of impingement apertures are defined on each impingement member.

Impingement cooling apparatus for turbomachine

A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum and that define injection holes therethrough. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. The mixing conduits fluidly couple the high-pressure plenum to the main passage, and the fluid from the fluid plenum is delivered with the high-pressure fluid to the main passage, where the fluids mix before being discharged from an outlet of the main passage. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.

Fluid mixing apparatus using high- and low-pressure fluid streams

Integrated combustor nozzles and turbomachines are provided. An integrated combustor nozzle includes a cooling insert having a flange. The cooling insert further includes a first wall and a second wall that each define respective passages therein. The first wall and the second wall each extend from an open end defined within the flange to a closed end. The first wall and the second wall each include an impingement side spaced apart from a solid side. Each impingement side defines a plurality of impingement apertures configured to direct coolant from the respective passage towards a side wall of the combustion liner. The cooling inserts further includes a collection passageway that is defined between the solid sides of the first wall and the second wall.

Cooling insert for a turbomachine

The present disclosure is directed to a fuel injection module for a segmented annular combustion system. The fuel injection module includes a housing body, a fuel nozzle portion, and at least one fuel injection lance. The fuel nozzle portion is fluidly coupled to a fuel nozzle plenum within the housing body, and the at least one fuel injection lance is fluidly coupled to an injector fuel plenum within the housing body. In some cases, the fuel nozzle portion is a bundled tube fuel nozzle having one or more subsets of tubes. The fuel injection lances are positioned along a radial side of the housing body or circumferentially between two subsets of tubes. Liquid fuel cartridges extend through the fuel nozzle portion, the fuel injection lances, or both.

Fuel injection module for segmented annular combustion system

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Pittsburgh, PA, United States of America

Michael John Hughes