Delavan Inc.

Collins Engine Nozzles, Inc.

Hamilton Sundstrand Corporation

Other

Rolls-royce Corporation

Jason Allen Ryon

Lev Alexander Prociw

Brandon Phillip Williams

Vijay V Pujar

Gregory A Zink

Jacob Greenfield

Philip E O Buelow

Brett A Pfeffer

Murtuza Lokhandwalla

Todd Haugsjaahabink

Charles E Reuter

Philip E Buelow

Steve Jay Myers

Joseph Samo

Steven Jay Myers

Pete J Schnoebelen

John Earl Short

Jay W Kokas

Richard E Versailles

Mark Alan Caples

Russell P Rourke

Michael Ferrarotti

Adrian L Stoicescu

Thomas J Ocken

Andy W Tibbs

Neal A Thomson

David H Bretz

Kevin D Gibbons

Matthew Donovan

Shawn Karl Reynolds

Steven L Smith

Nicole L Nelson

Jesse C Peters

Daniel Edward Bleeker

Raffi O Mangoyan

Robert Russell Fogarty

David Saltzman

Troy Finton

Ousmane Gaye

Viraphand Cholvibul

Gary W Chew

John David Canny

Roger A Seei

Andy M Tibbs

Lev A Prociw

Kevin Gibbons

Michael J Bronson

Fouad T Khairallah

Chien-Jung Yu

Lev Prociw

Brandon Phillips Williams

Mark A Caples

Brandon Phillip William

Brandon Philllip Williams

Lev Alexandder Prociw

Brandon Philip Williams

Steve Myers

Fouad Khairallah

Philip EO Buelow

Mark Caples

Steven J Myersw

Matt Raymond Donovan

Brett Alan Pfeffer

Phillip EO Buelow

A combustor assembly for a turbomachine includes a combustor housing defining a combustion chamber. The combustor housing includes an inlet portion, an outlet portion, and an axial axis extending between the inlet portion and the outlet portion. A first annular plenum is arranged at the inlet portion. The first annular plenum includes a first inlet and a first outlet. A second annular plenum radially spaced from the first annular plenum is arranged at the inlet portion. The second annular plenum includes a second inlet, a second outlet, a vortex inducing member arranged between the second inlet and the second outlet, and a fuel outlet. The second outlet includes a pre-filming surface that forms an annular ring of fuel that enters the second annular plenum through the fuel outlet and passes from the second annular plenum into a swirling fluid passing through the first outlet and the second outlet.

Combustor assembly including a fuel injection system for a turbomachine

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 system includes a combustor for a gas turbine defining a main axis extending in an upstream-downstream direction, the combustor including a combustor dome bounding an upstream portion of the combustor, wherein a plurality of injector openings are defined through the combustor dome. An injector defines a spray axis aligned with one of the plurality of injector openings for issuing a spray into the combustor along the spray axis. An actuator is operatively connected to the injector for movement of the injector relative combustor dome to adjust a relative position of the spray axis relative to the main axis to alter the position and/or direction of the spray injector during operation of the gas turbine engine.

Positional control of fuel injection into gas turbine combustors

A system includes an engine case for a gas turbine engine defined around a longitudinal axis. An access opening is defined through the engine case for access from outside the engine case to a space inside the engine case. A combustor is housed in the space inside the engine case. The combustor includes an inner annular wall and an outer annular wall radially outboard from the inner annular wall. The inner annular wall includes a first rail on an upstream end thereof. The outer annular wall includes a second rail on an upstream end thereof. The first and second rails each include a respective access portion configured to receive line replaceable injector components from through the access opening of the engine case into the first and second rails to form a combustor dome of the combustor.

Line replaceable fuel injector panels with single hatch installation

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 of making a fluid injection component for a gas turbine engine includes depositing material onto a piece of tube stock. The method includes machining an elbow into the deposited material, wherein machining the elbow includes forming a braze joint surface in the deposited material. Depositing can include laser cladding the material onto the piece of tube stock.

Material deposition for fuel nozzle joint

A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal. The auxiliary fuel circuit joins with the secondary fuel circuit for delivery to a fuel nozzle.

Proportional restriction of a secondary circuit of a fuel injector

A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet in response to fuel pressure received at the fuel inlet. Primary and secondary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the primary circuit, adapted and configured to actively control fuel through the primary circuit in response to a control signal.

Variable restriction of a fuel circuit of a fuel nozzle

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 fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal.

Proportional restriction of fuel nozzle with an auxiliary circuit

A fuel injector assembly can include a housing structure defining a circular shape, and one or more fuel injectors disposed in and/or formed integrally with the housing structure. The housing structure can be configured to angle the one or more fuel injectors in a direction such that the one or more fuel injectors effuse flow in a vector having a tangential flow component.

Fuel injectors assemblies with tangential flow component

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

A system includes an engine case for a gas turbine engine defined around a longitudinal axis. A combustor is housed in the space inside the engine case. The combustor includes an inner annular wall and an outer annular wall radially outboard from the inner annular wall. The inner annular wall includes a first rail on an upstream end thereof with a radially outward opening slot. The outer annular wall includes a second rail on an upstream end thereof. The combustor includes a plurality of circumferentially spaced apart dome liners extending from the first rail to the second rail. A plurality of fuel injector components can be assembled across the first and second rails to form a combustor dome together with the dome liners at an upstream end of a combustion space defined between the inner and outer annular walls of the combustor.

Line replaceable fuel injector panels

A method of making a fluid injector for a gas turbine engine includes depositing material onto a piece of tube stock. The method includes machining the deposited material into a fluid injector component. Depositing can include laser cladding the material onto the piece of tube stock. The method can include placing or flowing braze into a braze joint location between the deposited material and another fluid injector component and forming the braze into a braze joint in the braze joint location.

Material deposition for fluid injectors

Growing community of inventors

Carlisle, IA, United States of America

Jason Allen Ryon