United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Other

Timothy S Snyder

James B Hoke

Lawrence A Binek

Frank J Cunha

William Arthur Sowa

Robert M Sonntag

Albert K Cheung

Francisco J Cunha

Randal G McKinney

Stanislav Kostka, Jr

Joey Wong

Won-Wook Kim

Thomas J Rosfjord

Steven Wayne Burd

Stephen Karl Kramer

Jonathan Jeffery Eastwood

Zhongtao Dai

Joel H Wagner

Sean R Jackson

John S Tu

James P Bangerter

Nurhak Erbas-Sen

Stephen A Morford

Fumitaka Ichihashi

Kristin Kopp-Vaughan

George F Titterton, Iii

David Kwoka

John R Buey

Anthony Van

Christopher R Brdar

Randolph J Smith

Crisen McKenzie

Kevin J Van Dyke

Tracy A Propheter-Hinckley

Dominic J Mongillo, Jr

Mark F Zelesky

Carey J Clum

Jesse R Boyer

Jose R Paulino

Dennis M Moura

Lance L Smith

Steven H Zysman

Sean C Emerson

Andrew S Aggarwala

Alexander W Williams

Monica Pacheco-Tougas

William M Proscia

Roger O Coffey

Peter Cocks

Jeffrey Jay Lienau

Ryan Lundgreen

Donald J Hautman

John B McVey

Steven A Lozyniak

Justin M Locke

Aaron S Hu

Jeffrey M Cohen

Barry C Schlein

Baris A Sen

Dennis John Duhamel

Bruce V Johnson

Dibesh D Joshi

Christos Adamopoulos

David A Burns

Randolph T Lyda

Nicholas Mule

Richard E Gacek

Edward J McCoomb

Michael P Ross

Lourdes M Tafur Bermudez

William Proscia

Jeff S Noall

Antony Van

Brandon P Williams

Dennis J Duhamel

An assembly is provided for a turbine engine. This turbine engine assembly includes a flowpath duct, a fuel injector assembly and a secondary duct. The flowpath duct includes a flowpath. The fuel injector assembly includes an inner flow passage. The fuel injector assembly is configured to mix fuel with first gas within the inner flow passage to provide a fuel-gas mixture. The fuel injector assembly is configured to direct a jet of the fuel-gas mixture into the flowpath. The secondary duct is configured to direct second gas into the flowpath about the jet of the fuel-gas mixture.

Supplemental thrust system for a gas turbine engine

An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.

Fuel injector assembly for a turbine engine

A combustor may comprise an outer combustor panel and an inner combustor panel radially inward of the outer combustor panel. A bulkhead panel may extend radially between the outer combustor panel and the inner combustor panel. An outer spacer may be located between an outer flange of the bulkhead panel and the outer combustor panel. An inner spacer may be located between an inner flange of the bulkhead panel and the inner combustor panel.

Extended bulkhead panel

A fuel nozzle guide assembly for a gas turbine engine is provided. The fuel nozzle guide assembly includes a housing; a tube arranged in the housing and defining a portion of a first fluid passage therein, the first fluid passage configured to include a first fluid, wherein a second fluid passage is defined, in part, between an exterior surface of the tube and an interior surface of the housing, the second fluid passage configured to include a second fluid; an air inflow tube, the air inflow tube defining a central air passage and configured to include a third fluid; an air inflow assembly defining a third fluid passage and configured to include a fourth fluid; and a nozzle outlet configured to receive each of the first fluid, the second fluid, the third fluid, and the fourth fluid to cause mixing thereof.

Steam cooled hood injector

A combustor panel is disclosed herein. The combustor panel includes a top side, a bottom side opposite the top side, a feature coupled to the top side and extending orthogonally away from the top side, the feature defining a first space on the bottom side beneath the feature, a first plurality of cooling holes extending in a first direction from the top side to the bottom side, a second plurality of cooling holes extending in a second direction from the top side to the bottom side, the second direction being rotated about 1° to about 60° counter-clockwise from the first direction, and a third plurality of cooling holes extending in a third direction from the top side to the bottom side, the third direction being about rotated 1° to about 60° clockwise from the first direction.

Stud film cooling for double wall combustors

A fuel delivery system for a combustor of a gas turbine engine including a primary fuel tank configured to store a primary fuel, a secondary fuel tank configured to store a secondary fuel, a swirler configured to produce a main flame within a combustion chamber of the combustor, and a fuel nozzle configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet that is located proximate to an end of the swirler or at the end of the swirler, the end of the swirler being located at an inlet of the combustor. The fuel delivery system also includes a primary fuel line fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line fluidly connecting the secondary fuel tank to the swirler.

Method of using a primary fuel to pilot liquid fueled combustors

An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector aperture and a fuel supply passage. The injector aperture extends longitudinally through the engine structure along a centerline. The fuel supply passage extends laterally within the engine structure to the injector aperture. The fuel injector is mated with the injector aperture. The fuel injector includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along the centerline within the fuel injector to the nozzle orifice. The nozzle passage is fluidly coupled with the fuel supply passage.

Modular injector bolt for an engine

Fuel injectors for gas turbine engines include a housing and a tube defining a portion of a first fluid passage therein and a second fluid passage is defined between an exterior surface of the tube and an interior surface of the housing. An inner airflow tube is arranged having an inflow vane assembly and a central air passage. A portion of the first fluid passage extends axially at a position radially outward from the inner airflow tube, and the third fluid passage extends axially at a position radially outward from the first fluid passage. A nozzle outlet is configured to receive first, second, and thirds fluids from the respective fluid passages to cause mixing thereof. The inflow vane assembly comprises a number of vanes, with each vane angled relative to a nozzle axis at an angle between 20° and 40°.

Multi-fueled, water injected hydrogen fuel injector

Fuel injectors for gas turbine engines include an inner housing having a center body installed within the inner housing, an intermediate housing arranged radially outward from the inner housing, and an outer housing arranged radially outward from the intermediate housing. The center body is a hollow body structure defining a center body airflow passage therethrough, a first fluid passage is partially defined between an outer surface of the inner housing and an inner surface of the intermediate housing, a second fluid passage is partially defined within the intermediate housing, and a third fluid passage comprises the center body airflow passage, an inner airflow passage defined between an exterior surface of the center body and an interior surface of the inner housing, and an outer airflow passage that is defined by the outer housing and radially outward from the intermediate housing.

Liquid and hydrogen/methane fuel injector

An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

Multi-fuel, fuel injection system for a turbine engine

A combustor for a gas turbine engine includes a combustor liner, a fuel swirler integral and conformal with the combustor liner to provide an outlet for fuel into the combustor, and a dilution chute surrounding the fuel swirler outlet and extending into the combustor to provide a wetting surface for fuel exiting the fuel swirler.

Integrated fuel swirlers

An assembly is provided for a gas turbine engine. This assembly includes a combustor and a fuel conduit. The combustor includes a combustor wall that forms a peripheral boundary of a combustion chamber within the combustor. The fuel conduit extends along and is formed integral with the combustor wall. The fuel conduit is disposed outside of the combustion chamber.

Gas turbine engine combustor with integral fuel conduit(s)

An apparatus is provided for a turbine engine. This apparatus includes a fuel conduit and a fuel nozzle. The fuel conduit includes a supply passage. The fuel nozzle includes a nozzle passage, an end wall and a nozzle orifice. The nozzle passage has a longitudinal centerline and extends longitudinally through the fuel nozzle along the longitudinal centerline from the end wall to the nozzle orifice. The nozzle passage is configured with a convergent portion and a throat portion. The nozzle passage converges radially inward towards the longitudinal centerline as the convergent portion extends longitudinally along the longitudinal centerline away from the end wall and towards the throat portion. The supply passage is fluidly coupled to the nozzle passage by a fuel aperture in the end wall. A centerline of the fuel aperture is angularly and laterally offset from the longitudinal centerline.

A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. A hood chamber is separated from the combustion chamber by a bulkhead extending between the inner shell and the outer shell. The bulkhead includes at least one opening extending between the hood chamber and the combustion chamber. A fuel injector extends through the at least one opening. The fuel injector includes a primary fuel passage including a primary fuel outlet located within the combustion chamber. The fuel injector further includes a secondary fuel passage including a plurality of secondary fuel outlets located within the hood chamber.

Bluff-body piloted high-shear injector and method of using same

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Glastonbury, CT, United States of America

Timothy S Snyder