United Technologies Corporation

Raytheon Technologies Corporation

Woodward, Inc.

Kevin Joseph Low

James P Bangerter

Russell B Hanson

Joey Wong

James B Hoke

Jonathan Jeffery Eastwood

Nurhak Erbas-Sen

Jonathan M Jause

David Kwoka

Frank J Cunha

Brian S Tryon

Russell Albert Beers

John S Tu

Alexander W Williams

Robert M Sonntag

Aleksandar Kojovic

Seth A Max

Thomas R Russo

Sean D Bradshaw

Chris J Niggemeier

Sander G Niemeyer

Reza Rezvani

Scott A Ladd

Dennis John Duhamel

Andrew Manninen

Jose E Ruperte Sanchez

Jonathan Jeffrey Eastwood

A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.

Fuel nozzle for a gas turbine engine

A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.

Gas turbine engine wall assembly with offset rail

A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.

Gas turbine engine wall assembly with support shell contour regions

A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages that define an angle &#x3b1; with respect to a hot side of the bulkhead support shell and a second multiple of cooling impingement passages that define an angle &#x3b2; with respect to the hot side of the bulkhead support shell. The angle &#x3b1; is different than the angle &#x3b2;.

Gas turbine engine combustor bulkhead assembly

A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first and the second liner panel side edges are non-perpendicular to the liner panel forward and aft edge edges.

Swept combustor liner panels for gas turbine engine combustor

A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.

Combustor panels having angled rail

A manifold fitting receiving radial and axial manifolds and providing two radial outlets is disclosed. The manifold fitting, when used in conjunction with a fuel injector and a combustor for a gas turbine engine, reduces the radial footprint of the fuel injector and thereby allows for a more compact engine. Additionally, the manifold fitting eliminates parts, reducing weight in the process, as compared to prior art fittings. Such reductions in size, parts count, and weight are particularly beneficial for aircraft applications.

Single-fitting, dual-circuit fuel nozzle

A wall assembly is provided for a gas turbine engine. This wall assembly includes a support shell with a contoured region; and a multiple of liner panels mounted to the support shell. At least one of the multiple of liner panels includes an end rail. The contoured region is deformable to selectively contact at least a portion of the end rail. A method of assembling a wall assembly within a gas turbine engine is also provided. This method includes locating a stud that extends from a cold side of a liner panel through a support shell; and attaching a fastener onto the stud to at least partially close a gap defined between the panel and shell.

Gas turbine engine wall assembly interface

A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body. The seal alignment features are arranged such that there is only one alignment of the combustor seal with the turbine vane.

Combustor seal mistake-proofing for a gas turbine engine

A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell.

Combustor with grommet having projecting lip

A system for providing a seal between a combustor and a turbine vane. The system includes a flange configured to extend radially from the combustor, and a seal. The flange includes a flange surface configured to face in an axial direction toward a surface of the vane. The seal is configured to be axially loaded between the flange surface and the surface of the vane.

Combustor seal system for a gas turbine engine

A cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter.

Cooled combustor seal

A method for coating a turbine engine component comprises the steps of: providing a turbine engine component having at least one sacrificial attachment on a first side; grasping the turbine engine component via the at least one sacrificial attachment to position a first surface of the turbine engine component relative to a source of coating material; and applying a coating to said first side.

Method and system for holding a combustor panel during coating process

A fuel injector nozzle assembly includes a body extending along an axis and a core swirl plug positioned at least partially within the body. The core swirl plug has a flow modifying structure configured to swirl fuel at a location upstream from a distal end of the nozzle assembly.

Flow modifier for combustor fuel nozzle tip

A combustor assembly for a gas turbine engine includes a static structure and an annular combustor extending around a central axis and located radially inwards of the static structure. The annular combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber there between. The annular combustor is free of any rigid attachments directly between the static structure and the annular outer shell. The annular outer shell includes a radially-outwardly extending flange. A stop member is rigidly connected with the static structure and is located adjacent the radially-outwardly extending flange such that axial-forward movement of the annular combustor is limited.

Growing community of inventors

Portland, CT, United States of America

Kevin Joseph Low