General Electric Company

Ge Infrastructure Technology, LLC

Ge Vernova Infrastructure Technology LLC

Exxonmobil Upstream Research Company

General Electric Technology Gmbh

Willy Steve Ziminsky

Thomas Edward Johnson

William David York

Benjamin Paul Lacy

Christian Xavier Stevenson

Baifang Zuo

Gilbert Otto Kraemer

Jong Ho Uhm

Ertan Yilmaz

Lewis Berkley Davis, Jr

Abdul Rafey Khan

Balachandar Varatharajan

Derrick Walter Simons

Minesh Ashok Shah

Krishna Kumar Venkataraman

Patrick Benedict Melton

Geoffrey David Myers

Gregory Allen Boardman

Jonathan Dwight Berry

Lucas John Stoia

Ajai Singh

Arthur James Fossum

Michael John Hughes

David Kenton Felling

Pingchuan Wu

Heath Michael Ostebee

David August Snider

Avinash Vinayak Taware

Christopher Paul Keener

Mark Allan Hadley

John Joseph Lipinski

Scott Alan Kopcho

Sergey Anatolievich Meshkov

Mark P Bombard

Girard Albert Simons

Anthony Joseph Antonucci

Christopher Edward Wolfe

Kevin Weston McMahan

Ronald James Chila

Robert Joseph Iasillo

Fei Han

Timothy Andrew Healy

Sarah Lori Crothers

Ilya Aleksandrovich Slobodyanskiy

Eamon Patrick Gleeson

Bruce Gordon Norman

Joseph Vincent Citeno

Warren James Mick

Charles E Steber

John Charles Intile

Anthony Wayne Krull

Shiva Kumar Srinivasan

Jayaprakash Natarajan

Mark William Pinson

Chunyang Wu

Mahesh Bathina

Ravindra Annigeri

Jason Charles Terry

Balachandar Naidu

Sergey Adolfovich Oskin

Massoud Parisay

Eric Motter

Brock McLaren Wilson

Benjamin Paul Lacey

Avinash Vipayak Taware

John Stephen Henderson

Aparna Basker

Jr Lewis Berkley Davis

Charles Evan Steber

Shiva Srinivasan

Varatharajan Balachandar

A probe assembly for determining a clearance between a stationary component and a rotating component is provided. A gas turbine system and a related method are also provided. The probe assembly includes an elongated clearance tip extending from the stationary component toward the rotating component. A controller is configured to determine a clearance between the stationary component and the rotating component based on a known length of the elongated clearance tip extending from the stationary component at a time of contact with the rotating component. A tip advancement system is configured to advance a new elongated clearance tip toward the rotating component from the stationary component in response to the elongated clearance tip breaking from the contact with the rotating component.

Clearance probe assembly using replenishable, contacting elongated clearance tip

A method of operating a power plant is provided. The method includes generating, with the one or more power generators, a total plant power. The method further includes supplying, with a back up power source, a backup power output. The method further includes providing a first portion of the total plant power to one or more auxiliary devices to meet an auxiliary demand. The method further includes providing at least one of a second portion of the total plant power and the backup power output to the flexible firm skid to meet the flexible firm demand. The method further includes providing a third portion of the total plant power to a power grid outside of the power plant to meet a grid demand.

Power plant having a flexible firm skid

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

Systems and methods of detecting a fuel leak are provided. A method of detecting a fuel leak within a turbomachine combustor includes a step of monitoring, by a controller, a sensor output from a particulate matter sensor positioned on a component within the combustor. The sensor output includes one of a fault state sensor output or a non-fault state sensor output. The method further includes receiving, with the controller, the fault state sensor output from the particulate matter sensor when a fuel leak is present within the combustor.

Systems and methods for detecting a fuel leak

The present disclosure generally relates to a system with a gas turbine engine including a first combustor and a second combustor. The first combustor includes a first end cover with a first geometry and the second combustor includes a second end cover with a second geometry. The first geometry has one or more geometric differences relative to the second geometry.

System and method for control of combustion dynamics in combustion system

A system includes an oxidant compressor and a gas turbine engine turbine, which includes a turbine combustor, a turbine, and an exhaust gas compressor. The turbine combustor includes a plurality of diffusion fuel nozzles, each including a first oxidant conduit configured to inject a first oxidant through a plurality of first oxidant openings configured to impart swirling motion to the first oxidant in a first rotational direction, a first fuel conduit configured to inject a first fuel through a plurality of first fuel openings configured to impart swirling motion to the first fuel in a second rotational direction, and a second oxidant conduit configured to inject a second oxidant through a plurality of second oxidant openings configured to impart swirling motion to the second oxidant in a third rotational direction. The first fuel conduit surrounds the first oxidant conduit and the second oxidant conduit surrounds the first fuel conduit.

System and method for a fuel nozzle

An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

Integrated combustor and stage 1 nozzle in a gas turbine and method

The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles.

Variable volume combustor with an air bypass system

The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.

Variable volume combustor

A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes.

System and method for reducing combustion dynamics in a combustor

A combustor includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion.

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A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface. A plurality of tubes extends from the upstream surface through the downstream surface, and each tube provides fluid communication through the tube bundle. A baffle extends axially inside the tube bundle between adjacent tubes. A method for distributing fuel in a combustor includes flowing a fuel into a fuel plenum defined at least in part by an upstream surface, a downstream surface, a shroud, and a plurality of tubes that extend from the upstream surface to the downstream surface. The method further includes impinging the fuel against a baffle that extends axially inside the fuel plenum between adjacent tubes.

Combustor and method for distributing fuel in the combustor

Embodiments of the present application include a combustor assembly. The combustor assembly may include a combustion chamber, a first plenum, a second plenum, and one or more elongate air/fuel premixing injection tubes. Each of the elongate air/fuel premixing injection tubes may include a first length at least partially disposed within the first plenum and configured to receive a first fluid from the first plenum. Moreover, each of the elongate air/fuel premixing injection tubes may include a second length disposed downstream of the first length and at least partially disposed within the second plenum. The second length may be formed of a porous wall configured to allow a second fluid from the second plenum to enter the second length and create a boundary layer about the porous wall.

Systems and methods for preventing flashback in a combustor assembly

A turbomachine includes a compressor, a combustor operatively connected to the compressor, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a cap member having a first surface that extends to a second surface. The cap member further includes a plurality of openings. A plurality of bundled mini-tube assemblies are detachably mounted in the plurality of openings in the cap member. Each of the plurality of bundled mini-tube assemblies includes a main body section having a first end section and a second end section. A fluid plenum is arranged within the main body section. A plurality of tubes extend between the first and second end sections. Each of the plurality of tubes is fluidly connected to the fluid plenum.

Bundled multi-tube nozzle for a turbomachine

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Simpsonville, SC, United States of America

Willy Steve Ziminsky