General Electric Company

General Electric Technology Gmbh

Mark William Pinson

Lucas John Stoia

Willy Steve Ziminsky

Kevin Weston McMahan

Gregory Earl Jensen

Geoffrey David Myers

Ronald James Chila

Baifang Zuo

Donald Mark Bailey

David August Snider

Charles E Steber

John Charles Intile

Timothy James Purcell

Jayaprakash Natarajan

John Joseph Lynch

William Thomas Ross

Jason Charles Terry

Larry Lou Thomas

Sachin Khosla

Robert Walter Arnold

Steven C Castellaw

Neal Spencer Birchfield

Christopher Grant Cooper

Tapie Rohm

Ronald Thomas Clawson

Mark Mitchell

A method of igniting liquid fuel in a turbomachine combustor is provided. The method includes a step of initiating a flow of gaseous fuel from a gaseous fuel supply to a gaseous fuel nozzle. The method further includes a step of initiating a flow of liquid fuel from a liquid fuel supply to a primary liquid fuel cartridge. After initiating both the flow of gaseous fuel and the flow of liquid fuel, the method includes a step of igniting the flow of gaseous fuel and the flow of liquid fuel with an igniter. The method further includes a step of terminating the flow of gaseous fuel from the gaseous fuel supply to the gaseous fuel nozzle.

Methods of igniting liquid fuel in a turbomachine

A combustion system includes a head end comprising a liquid fuel cartridge. The liquid fuel cartridge has liquid fuel injection ports and is configured to produce combustion products via a diffusion flame. A liner is configured to deliver the combustion products from the head end to an aft frame, and an injector having an outlet is located along the liner between the head end and the aft frame. The injector outlet delivers a stream of oxidant inwardly into the liner, such that a mixedness and a velocity of the combustion products are increased prior to the combustion products reaching the aft frame. A method of producing combustion products having characteristics of a premixed flame in a liquid fuel combustion system is also provided herein.

System and method for combusting liquid fuel in a gas turbine combustor with staged combustion

The present disclosure is directed to an end cover assembly for a combustor of a turbomachine. The end cover assembly includes an end cover and a bundled tube fuel nozzle assembly positioned downstream from the end cover. The bundled tube fuel nozzle assembly includes a plurality of fuel nozzle tubes. A flame detector sight tube couples to the end cover. The flame detector sight tube is aligned with one of the fuel nozzle tubes.

Turbomachine combustor end cover assembly with flame detector sight tube collinear with a tube of a bundled tube fuel nozzle

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

A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage. The first swirler vane provides a first wake region within the flow segment. The second swirler vane provides a second wake region within the flow segment. A fuel injection peg is disposed downstream from the first swirler vane and the second swirler vane. The fuel injection peg is positioned within the flow segment between the first wake region and the second wake region.

Fuel nozzle having swirler vane and fuel injection peg arrangement

A method of operating a combustor having a central nozzle and a plurality of outer nozzles surrounding the central nozzle is provided. The method includes providing a liquid fuel to only the plurality of outer nozzles at a specified total energy input. The method includes decreasing the liquid fuel to the plurality of outer nozzles while simultaneously increasing a gas fuel to the central nozzle and the plurality of outer nozzles to substantially maintain the specified total energy input. The method includes supplying a fuel-air ratio of the gas fuel to the central nozzle that exceeds a threshold value such that a central nozzle flame is anchored. An air-fuel ratio of the gas fuel to the plurality of outer nozzles is less than the threshold value such that a plurality of outer nozzle flames are lifted until a purge flow is supplied to the outer nozzles.

Method of operating a combustor from a liquid fuel to a gas fuel operation

A turbomachine includes a compressor, a turbine operatively connected to the compressor, and a combustion assembly fluidly connected between the compressor and the turbine. The combustion assembly includes an end cover including a plurality of fuel circuits, a fuel distributing flange fluidly connected to at least one of the plurality of fuel circuits, a nozzle assembly fluidly linked to the at least one of the plurality of fuel circuits, and a fuel distribution system configured and disposed to deliver fuel to the fuel distributing flange. The fuel distribution system is selectively activated to stage fuel delivery to the at least one of the plurality of fuel circuits at a pressure sufficient to achieve atomization at the nozzle assembly without requiring a supplemental atomization air flow prior to delivering fuel to others of the plurality of fuel circuits at a pressure to achieve atomization without requiring a supplemental atomization air flow.

System and method for distributing fuel in a turbomachine

Methods and systems for analyzing combustion dynamics of a combustor system in the time domain are provided. The combustor system includes an inlet pipe coupled in flow communication with a combustion chamber. The method includes determining a characteristic equation of a wave traveling in the inlet pipe, determining an acoustic pressure oscillation in the combustion chamber, and determining a pressure fluctuation in the inlet pipe using the characteristic equation and the determined acoustic pressure oscillation.

Methods and systems for analysis of combustion dynamics in the time domain

A swirler assembly. The swirler assembly may include a hub, a vane positioned on the hub, and a fuel supply passageway extending from the hub through the vane. The fuel supply passageway may include a substantially triangular shape.

Swirler assembly

A combustor having a combustion liner and at least one combustor orifice assembly, the combustor orifice assembly comprising a boss, an orifice plate that defines an orifice, the orifice plate having a bottom surface that is adapted to be received by the boss, and a retaining ring, whereby the orifice plate is retained between the retaining ring and the boss.

Growing community of inventors

Greer, SC, United States of America

Mark William Pinson