Delavan Inc.

Pratt & Whitney Canada Corp.

Collins Engine Nozzles, Inc.

United Technologies Corporation

Other

Hamilton Sundstrand Corporation

Lev Alexander Prociw

Jason Allen Ryon

Gregory A Zink

Brandon Phillip Williams

Harris Shafique

Jacob Greenfield

Philip E O Buelow

Joseph Horace Brand

Aleksandar Kojovic

Parham Zabeti

Tin Cheung John Hu

Steve Jay Myers

Steven Jay Myers

Aleksander Kojovic

Jun Shi

Haralambos Cordatos

Parthasarathy Sampath

Joseph Samo

Shaoluo L Butler

Frank Whittaker

Neil Smith

Timothy Griffith

Oleg Morenko

Bhawan Bhai Patel

David C Jarmon

Eduardo David Hawie

Jason Araan Fish

Richard Alan Kostka

Andy W Tibbs

Michael J Dowhan

Philip E Buelow

Kevin Eugene Thompson

Dany Clarence Gaudet

Steven L Smith

Claude Raymond Pelletier

John Sokalski

Alexsandar Kojovic

Charles E Reuter

Honza Stastny

Thomas J Ocken

Lafleche Gagnon

David J Bombara

Lee A Hoffman

Angelo Martucci

Scott J Beloncik

Victor Gandza

Roger Jonathan Gates

John D Cannata

Nicole L Nelson

Bastien Ste Marie

Rolando Buenafe Acolacol

Giovanni Mario Mulas

Pierre Juteau

David C Jamon

Andy M Tibbs

Alekaandar Kojovic

Patrice Fiset

Roger A Seei

Fouad T Khairallah

Michael J Bronson

Tin Cheung Hu

Brandon Phillips Williams

Brandon Philllip Williams

Brandon Philip Williams

Fouad Khairallah

Philip EO Buelow

Steven J Myersw

Steven J Myers

A combustor dome system includes an annular combustor dome defining a main axis therethrough. The combustor dome includes opposed upstream and downstream faces, wherein the upstream face is configured to face upstream toward a compressor discharge space, wherein the downstream face is configured to face downstream toward a combustor space. The downstream face has a curved cross-sectional profile. A plurality of nozzles extends at least partially through the combustor dome from the upstream face to the downstream face for injection of fuel into the combustor space. A fuel manifold is in fluid communication with the plurality of nozzles.

Fuel injectors for multipoint arrays

A torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.

Fuel systems for torch ignition devices

A method includes forming fluid conduit inside a heat shield in an additive manufacturing process, removing powder from an interior passage of the fluid conduit and from an insulation gap defined between the fluid conduit and the heat shield, separating the heat shield and fluid conduit from the build platform, and shifting the fluid conduit to a shifted position relative to the heat shield. The method includes securing the fluid conduit to the heat shield in the shifted position.

Fluid conduits with heat shielding

A multipoint fuel injection system comprises an injection system segment including a circumferentially extending outer support defining a fuel manifold with a plurality of manifold passages extending circumferentially therethrough. A first connector is included at a first circumferential end of the outer support and a second connector is included at a second circumferential end of the outer support opposite the first circumferential end. The first and second connectors are each configured to connect each manifold passage with a manifold passages of a respective outer support of a circumferentially adjacent injection system segment. The system includes a circumferentially extending inner support and a plurality of circumferentially spaced apart feed arms extending radially between the inner support and the outer support. A plurality of outlet openings extend in an axial direction from each feed arm for feeding respective injection nozzles.

Sectional fuel manifolds

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.

Surface igniter cooling system

An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The torch igniter is situated such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case.

Radially oriented internally mounted continuous ignition device

A method includes forming a fluid conduit inside a heat shield in an additive manufacturing process, wherein a fluid nozzle is defined at a downstream end of the fluid conduit, and wherein the heat shield is formed about the fluid nozzle. The method includes removing powder from an interior passage of the fluid conduit and fluid nozzle and from an insulation gap defined between the heat shield and the fluid conduit and fluid nozzle. The method includes separating the heat shield, fluid conduit, and fluid nozzle from the build platform. The method includes shifting the fluid conduit and fluid nozzle to a shifted position relative to the heat shield, and securing the fluid conduit and fluid nozzle to the heat shield in the shifted position.

Fluid nozzles with heat shielding

A heat transfer arrangement includes two or more heat transfer cells. The heat transfer cells together define a boundary between a higher temperature region and a lower temperature region. Each of the two or more heat transfer cells includes two or more walls defining a fluid tight cavity. One or more wick is fused to an inner surface of one or more of the walls to wick liquid from a lower temperature portion of the cavity to a higher temperature portion of the cavity. Combustors having heat transfer arrangements with heat transfer cells and methods of making heat transfer arrangements are also described.

Heat transfer arrangements and methods of making heat transfer arrangements

An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.

Torch igniter cooling system

A fuel system includes a fuel supply system. A plurality of fuel nozzles are connected in fluid communication with the fuel supply system to supply fuel from a fuel source to be issued for combustion from the fuel nozzles. A cooling system is included, wherein at least one of the fuel nozzles includes a cooling circuit in addition to a fuel circuit for issuing fuel from the fuel supply system for combustion. The cooling circuit includes an inlet and an outlet. The inlet is in fluid communication with the cooling system for circulation of coolant through the cooling circuit and back to the cooling system out the outlet of the cooling circuit for cooling the fuel circuit with the fuel circuit staged off.

Cooling in staged fuel system

A fuel injector system for a torch igniter includes an injector body centered on an axis, a receiving aperture formed in a cap of the torch igniter, an injector aperture, an air channel, a fuel channel, and a purge passage formed in a housing of the torch igniter and fluidly connected to a cooling air source. The injector body includes an axial wall at a first axial end of the injector body, an outer wall connected to the axial wall and extending along the axis transverse to the first wall, and an inner portion connected to the axial wall and extending along the axis transverse to the axial wall. An outer surface of the inner portion is spaced a distance from an inner surface of the outer wall, forming an insulating space between the outer wall and the inner portion.

Fuel injector systems for torch igniters

A system includes an air manifold, a fuel manifold, and a plurality of fuel injectors. At least one of the fuel injectors includes a heat exchanger portion for supplying compressed, cooled air form the heat exchanger portion to the air manifold. An air valve is operatively connected to an outlet of the air manifold for controlling release of air from the air manifold. A controller is operatively connected to the air valve, wherein the controller includes machine readable instructions configured to control the air valve to regulate flow of air through the air valve based on fuel temperatures in the fuel channel. The machine readable instructions can be configured to cause the controller to flow air through the air valve in a heat exchange mode if a fuel temperature in the fuel injectors is below a predetermined fuel temperature.

Systems for fuel injectors with fuel air heat exchangers

A fluid nozzle includes a first fluid circuit, a second fluid circuit spaced apart from the first fluid circuit and a fuel circuit. The fuel circuit is defined between the first and second fluid circuits and between a first fuel circuit wall and a second fuel circuit wall. A ring-shaped permeable barrier is positioned between the first and second fuel circuit walls configured and adapted to provide a controlled resistance to fuel flow. A fuel distributor includes a first fuel circuit wall and a second fuel circuit wall spaced apart from the first fuel circuit wall. A fuel circuit is defined between the first and second fuel circuit walls. A ring-shaped permeable barrier is positioned between first and second fuel circuit walls. A combustion assembly includes a combustor housing, a combustor dome positioned at an upstream end of the combustor housing, and a fluid nozzle positioned adjacent the combustor dome.

Fluid distributors for fluid nozzles

An injection system includes an inner nozzle body defining a first air path along a longitudinal axis. The first air path defines a converging-diverging section between an upstream portion of the first air path and an outlet orifice of the first air path. A main orifice is defined at a narrowest portion of the converging-diverging section. A fuel circuit wall is outboard of the inner nozzle body. A fuel path is defined between the fuel circuit wall and the inner nozzle body. An outer nozzle body outboard of the fuel circuit wall has a second air path defined through the inner nozzle body for communication of air from the outer nozzle body into the first air path, wherein the second air path meets the first air path at a second orifice in the first air path downstream of the main orifice of the inner nozzle body.

Passive secondary air assist nozzles

Growing community of inventors

Johnston, IA, United States of America

Lev Alexander Prociw