Patents by Inventor Robert M. Sonntag
Robert M. Sonntag has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Patent number: 11175041Abstract: 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.Type: GrantFiled: October 10, 2019Date of Patent: November 16, 2021Assignee: Raytheon Technologies CorporationInventors: San Quach, John S. Tu, Robert M. Sonntag, Robert Selinsky, Jr., John J. Rup, Jr., Anthony Van
-
Patent number: 10844790Abstract: 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.Type: GrantFiled: February 7, 2019Date of Patent: November 24, 2020Assignee: Raytheon Technologies CorporationInventors: James B. Hoke, Timothy S. Snyder, David Kwoka, Robert M. Sonntag
-
Patent number: 10563584Abstract: 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.Type: GrantFiled: October 27, 2017Date of Patent: February 18, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jason Shenny, John J. Rup, Jr., Robert M. Sonntag, James B. Hoke, San Quach, Richard G. Ullrich
-
Publication number: 20200041125Abstract: 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.Type: ApplicationFiled: October 10, 2019Publication date: February 6, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: SAN QUACH, JOHN S. TU, ROBERT M. SONNTAG, ROBERT SELINSKY, JR., JOHN J. RUP, JR., ANTHONY VAN
-
Patent number: 10551065Abstract: 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.Type: GrantFiled: May 26, 2016Date of Patent: February 4, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Jeffery Eastwood, Joey Wong, Robert M. Sonntag, Albert K. Cheung, Timothy S. Snyder
-
Publication number: 20200025090Abstract: 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.Type: ApplicationFiled: February 7, 2019Publication date: January 23, 2020Inventors: James B. Hoke, Timothy S. Snyder, David Kwoka, Robert M. Sonntag
-
Patent number: 10480788Abstract: 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.Type: GrantFiled: August 16, 2016Date of Patent: November 19, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: San Quach, John S. Tu, Robert M. Sonntag, Robert Selinsky, Jr., John J. Rup, Jr., Anthony Van
-
Patent number: 10386067Abstract: 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.Type: GrantFiled: September 15, 2016Date of Patent: August 20, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: San Quach, Scott A. Elliott, Robert M. Sonntag, John S. Tu, Anthony Van, Joseph J. Sedor, Robert Selinsky, Jr., John J. Rup, Jr., Neil B. Ridgeway, Gerard V. Cadieux, Jeffrey Leon, Monica Pacheco-Tougas, Lisa A. Jenkins, Lisa Tse, Andrew Cervoni, Frank J. Trzcinski
-
Publication number: 20190128187Abstract: 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.Type: ApplicationFiled: October 27, 2017Publication date: May 2, 2019Inventors: Jason Shenny, John J. Rup, JR., Robert M. Sonntag, James B. Hoke, San Quach, Richard G. Ullrich
-
Patent number: 10240533Abstract: 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.Type: GrantFiled: March 15, 2013Date of Patent: March 26, 2019Assignee: United Technologies CorporationInventors: James B. Hoke, Timothy S. Snyder, David Kwoka, Robert M. Sonntag
-
Publication number: 20180283695Abstract: A gas turbine engine and a combustor panel assembly are disclosed. The gas turbine engine includes a combustor panel with a panel dilution hole formed therethrough, a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material, and a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.Type: ApplicationFiled: April 3, 2017Publication date: October 4, 2018Inventors: San Quach, Robert M. Sonntag, Donald W. Peters
-
Publication number: 20180073737Abstract: 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.Type: ApplicationFiled: September 15, 2016Publication date: March 15, 2018Inventors: San Quach, Scott A. Elliott, Robert M. Sonntag, John S. Tu, Anthony Van, Joseph J. Sedor, Robert selinsky, JR., John J. Rup, JR., Neil B. Ridgeway, Gerard V. Cadieux, Jeffrey Leon, Monica Pacheco-Tougas, Lisa A. Jenkins, Lisa Tse, Andrew Cervoni, Frank J. Trzcinski
-
Publication number: 20180051879Abstract: 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.Type: ApplicationFiled: August 16, 2016Publication date: February 22, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: SAN QUACH, JOHN S. TU, ROBERT M. SONNTAG, ROBERT SELINSKY, JR., JOHN J. RUP, JR., ANTHONY VAN
-
Patent number: 9897319Abstract: 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.Type: GrantFiled: February 25, 2015Date of Patent: February 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Robert M. Sonntag, Michael Youssef, Edward B. Harris, Richard A. Long
-
Patent number: 9476591Abstract: A combustion chamber louver assembly includes an aft louver having a forward panel 24 that extends axially from a louver leading edge 26 to a corner 28, and a forward louver joined to the forward panel of the aft louver. A lip 48 defined by a portion of the forward louver that extends axially past the corner to a louver trailing edge 36 includes circumferentially distributed trailing edge slots 60 extending forwardly from the trailing edge a nominal distance equal to about 88% to 95% of the length L of the lip.Type: GrantFiled: March 14, 2006Date of Patent: October 25, 2016Assignee: United Technologies CorporationInventors: Mark Edward Tuttle, Robert M. Sonntag, John H. Nixon
-
Publication number: 20160273773Abstract: 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.Type: ApplicationFiled: May 26, 2016Publication date: September 22, 2016Inventors: Jonathan Jeffery Eastwood, Joey Wong, Robert M. Sonntag, Albert K. Cheung, Timothy S. Snyder
-
Publication number: 20160258623Abstract: The present disclosure relates to combustor and heat shield configurations for gas turbine engines. A heat shield for a gas turbine engine can include one or more effusion holes downstream of a dilution hole to restore a cooling film applied to the heat shield in the combustor. Effusion holes may be clustered in one or more configurations and rows following each dilution hole and/or on a trailing edge of each heat shield panel structure. One or more embodiments are directed to effusion holes positioned along a trailing edge of a heat shield panel.Type: ApplicationFiled: March 5, 2015Publication date: September 8, 2016Inventors: James S. TU, James B. HOKE, Robert M. SONNTAG, Timothy S. SNYDER
-
Publication number: 20160245517Abstract: 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.Type: ApplicationFiled: February 25, 2015Publication date: August 25, 2016Inventors: Robert M. SONNTAG, Michael YOUSSEF, Edward B. HARRIS, Richard A. LONG
-
Patent number: 9377198Abstract: 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.Type: GrantFiled: February 17, 2012Date of Patent: June 28, 2016Assignee: United Technologies CorporationInventors: Jonathan Jeffery Eastwood, Joey Wong, Robert M. Sonntag, Albert K. Cheung, Timothy S. Snyder
-
Patent number: 9052111Abstract: 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.Type: GrantFiled: June 22, 2012Date of Patent: June 9, 2015Assignee: United Technologies CorporationInventors: Nurhak Erbas-Sen, James B. Hoke, Albert K. Cheung, Robert M. Sonntag, Timothy S. Snyder