United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Woodward, Inc.

James B Hoke

Timothy S Snyder

Albert K Cheung

John S Tu

Monica Pacheco-Tougas

Stephen Karl Kramer

Robert M Sonntag

Randal G McKinney

William Arthur Sowa

Steven Wayne Burd

Dennis M Moura

Fumitaka Ichihashi

Alan J Goetschius

David Kwoka

Tracy A Propheter-Hinckley

Brandon W Spangler

Steven Bruce Gautschi

Jonathan Jeffery Eastwood

Atul Kohli

Ricardo Trindade

Dustin Wayne Davis

Kevin Joseph Low

James P Bangerter

Nurhak Erbas-Sen

Mark F Zelesky

San Quach

Frank J Cunha

Scott D Lewis

Zhongtao Dai

Stanislav Kostka, Jr

Robert Sze

Benjamin Bellows

Joseph D Coughlan, Iii

Reid Dyer Curtis Smith

Anthony Van

Philip J Kirsopp

Dennis John Duhamel

Trevor Rudy

John T Ols

Alexander W Williams

Jeffrey Mark Cohen

William M Proscia

Aleksandar Kojovic

Dave J Hyland

John J Rup, Jr

Jeffrey Jay Lienau

Jonathan M Jause

Kristin Kopp-Vaughan

Sean D Bradshaw

Jason Shenny

Sander G Niemeyer

Won-Wook Kim

David J Hyland

Reza Rezvani

Timothy J Gaudet

Thomas A Bush

Daryl B Mountz

Victor M Pinedo

Christos Adamopoulos

David A Burns

Irving Segalman

Howard Olsen

Richard G Ullrich

Kenneth S Siskind

Reid D C Smith

William Proscia

Jason M Gringhaus

Aaron J Dornback

Andrew Manninen

Dae K Dempsey

Matthew G Van Eck

Benjamin D Bellows

Tracy A Propheter-Hinkley

Dennis J Duhamel

Randal G Mckinney

Jonathan Jeffrey Eastwood

Iii Joseph D Coughlan

Joseph D Coughlan Iii

Joseph D Iii Coughlan

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 gas turbine engine component includes a first surface and a second surface. The component further includes a dilution hole defined by the first surface and the second surface. The component further includes a first effusion hole and a second effusion hole each having an inlet defined by the second surface and an outlet defined by the first surface such that the outlet of the first effusion hole is located nearer to the dilution hole than the outlet of the second effusion hole.

Effusion cooling for dilution/quench hole edges in combustor liner panels

In accordance with one aspect of the disclosure, a combustor is disclosed. The combustor may include a shell and a liner disposed within the shell. The combustor may further include a grommet at least partially defining a hole communicating through the shell and liner and a cooling channel communicating through the grommet.

Combustor cooled quench zone array

A liner assembly for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the liner assembly includes a panel defining a left side and a right side and a hot side and a cold side, the panel having a dilution hole and a plurality of effusion holes extending between the hot side and the cold side. In various embodiments, the plurality of effusion holes includes a first subgrouping of effusion holes disposed downstream of the dilution hole and aligned in a generally left to right orientation toward a dividing line extending downstream of the dilution hole and a second subgrouping of effusion holes disposed downstream of the dilution hole and aligned in a generally right to left orientation toward the dividing line extending downstream of the dilution hole.

Combustor panel

A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.

Combustor with axial staging for a gas turbine engine

A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.

Contoured dilution passages for gas turbine engine combustor

A combustor panel may comprise a dilution hole, a plurality of film cooling holes each of the plurality comprising an inlet and an outlet, a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, wherein each of film cooling holes of the first group have a first outlet angle oriented radially toward the center of the dilution hole, and a second group of the plurality of film cooling holes arranged radially outward of the first group and relatively circumferentially between the first group.

Dilution/effusion hole pattern for thick combustor panels

A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.

Fuel distribution within a gas turbine engine combustor

A fuel injection system may comprise a mixer and a fuel injector disposed within the mixer. The mixer may comprise an outer housing with an exit port and a bluff body extending across the exit port of the outer housing. A flared surface of the mixer may match a contour of the bluff body.

Bluff body fuel mixer

A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

Washer for combustor assembly

A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

Cooling configurations for combustor attachment features

Growing community of inventors

Tolland, CT, United States of America

James B Hoke