General Electric Company

Gregory Allen Boardman

Pradeep Naik

Patrick Benedict Melton

Manampathy Gangadharan Giridharan

Clayton Stuart Cooper

Ronald James Chila

James Harold Westmoreland

Geoffrey David Myers

Joseph Zelina

Johnie Franklin McConnaughhay

Michael Anthony Benjamin

Ajoy Patra

Michael John Hughes

Sarah Lori Crothers

Hua Zhang

Allen Michael Danis

Douglas Frank Beadie

Hasan Ul Karim

Thomas Edward Johnson

Lucas John Stoia

Willy Steve Ziminsky

Gilbert Otto Kraemer

Donald Mark Bailey

Mark Allan Hadley

Jonathan Dwight Berry

Benjamin Paul Lacy

Kevin Weston McMahan

Perumallu Vukanti

David Martin Johnson

Wei A Chen

Saket Singh

Michael Terry Bucaro

Scott Robert Simmons

Jason Thurman Stewart

Jong Ho Uhm

Rimple Rakeshkumar Rangrej

R Narasimha Chiranthan

Derrick Walter Simons

David Albin Lind

Jeffrey Michael Martini

Vishal Sanjay Kediya

Nishant Govindbhai Parsania

Bassam Sabry Mohammad Abd El-Nabi

William Thomas Ross

Randall Charles Boehm

Ranjeet Kumar Mishra

Eric John Stevens

Gerardo Antonio Salazar Lois

Jayanth Sekar

Ting-Yu Tu

Rishikesh Prakash Karande

Bassam Sabry Mohammad Abdelnabi

Kapil Kumar Singh

Bryan Wesley Romig

Ertan Yilmaz

Joseph Vincent Citeno

Balachandar Varatharajan

Jun Cai

Ranganatha Narasimha Chiranthan

Mark David Durbin

Keith Robert McManus

Gregory Scott Means

William Thomas Bennett

William Francis Carnell, Jr

Valeria Proano Cadena

Fabien Thibault Codron

Kara Johnston Edwards

Narasimhan S Sahana

Douglas Downey Turner

Sravan Kumar Dheeraj Kapilavai

Jerome David Brown

Xiomara Irizarry-Rosado

Mathew Paul Thariyan

Marco Venturato

Carlo Antonio Arguinzoni

Jacob Foster

Kediya Vishal Sanjay

Azardokht Hajiloo

Christine Elaine Simu

Rajesh Sharma

Gerardo Antonio Salazar-Lois

Keith Robert Mcmanus

Geoffrey Davis Myers

Rishikesh Karande

Greffrey David Meyers

Johnie F Mcconnaghhay

A premixer for a combustor includes: a centerbody having a hollow interior cavity; a swirler assembly radially outward of the centerbody; a peripheral wall disposed radially outward of the centerbody and the swirler assembly such that a mixing duct is defined between the peripheral wall and the centerbody, downstream from the swirler assembly; an annular splitter radially inward of the swirler assembly and radially outward of the centerbody such that a radial gap is defined between the splitter and an outer surface of the centerbody, wherein the splitter includes a trailing edge which extends axially aft of the swirler assembly; a fuel gallery disposed inside the interior cavity of the centerbody; and at least one fuel injector extending outward from the fuel gallery and passing through an injector port communicating with the outer surface of the splitter.

Premixer for a combustor

A mixer for blending fuel and air in a combustor of a turbine engine. The mixer includes a central body having a central passageway and a central axis. The mixer includes a plurality of tubes positioned radially around the central axis and circumferentially around a periphery of the mixer. Each of the tubes of the mixer includes opposed openings and a tangential opening. Each of the tubes of the mixer includes a cylindrical interior mixing passage configured to receive air flow from the opposed openings and the tangential opening and a fuel flow. The opposed openings are configured to spread the fuel flow laterally and the tangential opening is configured to spread the fuel flow tangentially.

Gas turbine fuel mixer comprising a plurality of mini tubes for generating a fuel-air mixture

Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.

Trapped vortex combustor and method for operating the same

A premixer assembly for a combustor includes: at least one ring of premixers, each premixer having a central axis, an annular peripheral wall surrounding a centerbody, and at least one swirler disposed between the centerbody and the peripheral wall, wherein the peripheral wall defines an inlet area of the premixer; and a lip extending forward along the central axis from the peripheral wall, the lip extending at an oblique angle to the axis of symmetry.

Combustor premixer assembly including inlet lips

A combustor for a gas turbine engine has a combustor liner that has a cold surface side and a hot surface side, the liner defining an upstream end and a downstream end, and a dilution opening through the combustor liner. The dilution opening includes a main dilution hole portion having an upstream edge and a downstream edge, a notched portion disposed at the upstream edge and extending upstream from the upstream edge, the notched portion being in fluid communication with the main dilution hole portion, and a slotted portion disposed at the downstream edge and extending downstream of the downstream edge, the slotted portion being in fluid communication with the main dilution hole portion.

Dilution air inlets with notched tip and slotted tail for combustor

A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.

Volute trapped vortex combustor assembly

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.

Combustor fuel assembly

A pilot pre-mixer for a gas turbine engine has a pilot body that includes an internal mixing chamber, a first end on an upstream side of the internal mixing chamber, a second end on a downstream side of the internal mixing chamber, a fuel injector at the first end and communicable with the internal mixing chamber, a plurality of first oxidizer inlet ports arranged to provide an oxidizer agent from outside of the pilot body to the internal mixing chamber, and a plurality of pilot outlet ports at the second end and communicable with the internal mixing chamber, each of the plurality of pilot outlet ports having an outlet on the second end for dispensing a pilot fluid mixture into a combustion zone of a combustor.

Furcating pilot pre-mixer for main mini-mixer array in a gas turbine engine

A fuel injector and mini-mixer system includes a mixing element tube configured to mix air and fuel prior to injecting the air and fuel into a combustor, an injector positioned within the mixing element tube, the injector being configured to inject a fluid into the mixing element tube, one or more air inlet slots positioned on one or more sides of the injector, one or more fuel injection holes configured to inject fuel into the mixing element tube, and one or more delta wing vortex generators positioned within an internal wall of the mixing element tube, the one or more delta wing vortex generators configured to generate a vortex pair that accelerates the mixing of air and fuel injected into the mixing element tube. Additional air slots can be provided downstream of the delta wing vortex generators to energize the vortex pair or lift fuel away to prevent flameholding.

Fuel injector and pre-mixer system for a burner array

A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.

Premixer for low emissions gas turbine combustor

Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage. The fuel-oxidizer mixing passage is configured to provide a flow of fuel-oxidizer mixture to a combustion chamber via the outlet opening.

Combustion section and fuel injector assembly for a heat engine

A gas turbine engine including a trapped vortex combustor assembly is generally provided. The combustor assembly includes an inner liner wall extended annularly around a combustor centerline, and an outer liner wall extended annularly around the combustor centerline. The inner liner wall and the outer liner wall together define an involute wall extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The involute wall defines an involute combustion chamber. One or more of the inner liner wall and the outer liner wall each define a first dilution opening and a shaped dilution opening.

Involute trapped vortex combustor assembly

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Greer, SC, United States of America

Gregory Allen Boardman