United Technologies Corporation

Raytheon Technologies Corporation

Robert M Sonntag

Timothy S Snyder

James B Hoke

San Quach

John J Rup, Jr

Jonathan Jeffery Eastwood

Albert K Cheung

John S Tu

Joey Wong

David Kwoka

Anthony Van

Robert Selinsky, Jr

Steven Wayne Burd

Kevin W Schlichting

James P Bangerter

Reza Rezvani

Monica Pacheco-Tougas

Kevin Joseph Low

Nurhak Erbas-Sen

Jeffrey Leon

Frank J Trzcinski

Joseph James Sedor

Jonathan M Jause

Scott A Elliott

Neil B Ridgeway

Jason Shenny

Michael Youssef

Andrew Cervoni

Dennis John Duhamel

Daryl B Mountz

Gerard V Cadieux

Howard Olsen

Richard G Ullrich

Mark Edward Tuttle

John H Nixon

Lisa A Jenkins

Lisa Tse

Edward B Harris

Richard A Long

Jr John J Rup

Jr Robert Selinsky

Scott A Elliot

Dennis J Duhamel

Robert Selinsky Jr

John J Rup Jr

A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

Systems and methods for combustor panel

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

Combustor panels including panel bodies with first and second sides, a pin array extending from the first side, wherein each pin extends a first height, has a pin diameter, and is separated from adjacent pins by a pin array separation distance. A structural protrusion extends from the first side. No pins of the pin array are located within a flashing distance that is equal to a protrusion separation distance plus half of the pin diameter, wherein a location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. At least one pin array extension is integrally formed with the structural protrusion, the pin array extension extending along the first side to a position that replaces a pin of the pin array that would be within the flashing distance.

Float wall combustor panels having airflow distribution features

A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.

Heat shield for a combustor

A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

Wall panel assembly 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

The present disclosure relates combustor configurations for a gas turbine engine. In one embodiment, a combustor includes a combustor shell enclosing a first area of free space, and an igniter for the combustor shell, the igniter including a distal end. The combustor also includes one or more elements configured to retain the igniter and to interface with the combustor shell, wherein the igniter is retained that the distal end of the igniter is recessed from the first area of free space. According to another embodiment, a combustor configuration may include one or more elements configured to retain an igniter and interface with the combustor shell, wherein the one or more elements define a boundary between the combustor shell and one or more elements, and wherein the igniter is retained within the one or more elements such that the distal end of the igniter is recessed from the boundary.

Igniter position for a combustor of a gas turbine engine

A combustion chamber louver assembly includes an aft louver having a forward panelthat extends axially from a louver leading edgeto a corner, and a forward louver joined to the forward panel of the aft louver. A lipdefined by a portion of the forward louver that extends axially past the corner to a louver trailing edgeincludes circumferentially distributed trailing edge slotsextending forwardly from the trailing edge a nominal distance equal to about 88% to 95% of the length L of the lip.

Crack resistant combustor

A heat shield includes a panel having a forward face and an aft face, a circumferential outer side and a circumferential inner side such that the panel subtends a predetermined arc, and a first radially extending side and a second radially extending side each extending from the circumferential outer side to the circumferential inner side. The panel defines an opening extending between the forward face and the aft face, a lip projecting from the forward face and extending around the opening, a rail projecting from the forward face and extending around the lip to define a cavity region between the lip and the rail, and a plurality of holes in the cavity region. Each of the plurality of holes extends from the forward face to the aft face. A region of the panel extending from the lip to the circumferential outer side is free of any aft-projecting features.

A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The combustor heat shield includes shield quench apertures fluidly coupled with the shell quench apertures, first effusion apertures fluidly coupled with the first impingement apertures, and second effusion apertures fluidly coupled with the second impingement apertures. The shield quench apertures and the first effusion apertures are configured in a first axial region of the heat shield, and the second effusion apertures are configured in a second axial region of the heat shield located axially between the first axial region and a downstream end of the heat shield. A density of the first effusion apertures in the first axial region is greater than a density of the second effusion apertures in the second axial region.

Turbine engine combustor wall with non-uniform distribution of effusion apertures

A turbine engine assembly includes a combustor and a stator vane arrangement having a plurality of stator vanes. The combustor includes a combustor wall that extends axially from a combustor bulkhead to a distal combustor wall end, which is located adjacent to the stator vane arrangement. The combustor wall includes a support shell with a plurality of impingement apertures, and a heat shield with a plurality of effusion apertures. The combustor wall end includes a plurality of circumferentially extending film cooled regions. At least one of the film cooled regions is circumferentially aligned with one of the stator vanes and includes a cooling aperture.

Turbine engine combustor and stator vane assembly

An annular combustor includes an annular outer shell that includes a first flange that defines an inner diameter IDand an annular inner shell that includes a second flange that defines an outer diameter OD. An annular hood includes a radially outer hood flange and a radially inner hood flange. A bulkhead includes a radially outer bulkhead flange that defines an outer diameter ODand a radially inner bulkhead flange that defines an inner diameter ID. The first flange is secured at a radially outer joint between the radially outer hood flange and the radially outer bulkhead flange. The second flange is secured at a radially inner joint between the radially inner hood flange and the radially inner bulkhead flange. The IDand the ODdefine a ratio R1 of ID/ODthat is 0.998622-1.001129, and the IDand the ODdefine a ratio R2 of ID/ODthat is 0.998812-1.001388.

Annular combustor

An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

Thermal barrier coating

Growing community of inventors

Bolton, CT, United States of America

Robert M Sonntag