Patents by Inventor John S. Tu
John S. Tu 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: 11698005Abstract: Flow diverters for installation in mid-turbine frame systems at a conduit outlet of gas turbine engines are described. The flow diverters include a diverter body having a connector portion defining a diverter inlet, a diverter extension at least partially defining a diverter outlet, and a curved portion arranged between the connector portion and the diverter extension, the curved portion configured to change a direction of flow from a first direction to a second direction that is about 90° from the first direction as the flow passes from the diverter inlet to the diverter outlet.Type: GrantFiled: January 22, 2021Date of Patent: July 11, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: John S. Tu, Robert Newman, Paul K. Sanchez, Jeffrey J. Lienau, John T. Ols, Prabaharan Manoharan, Venu Sambarapu, Rajendra Prasad Uppara Allabanda
-
Patent number: 11236677Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.Type: GrantFiled: May 15, 2019Date of Patent: February 1, 2022Assignee: Raytheon Technologies CorporationInventors: Matthew Andrew Hough, John S. Tu, Stephen C. Harmon, Paul F. Croteau, Russell B. Hanson, Joshua C. Rathgeb
-
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
-
Publication number: 20210246832Abstract: Flow diverters for installation in mid-turbine frame systems at a conduit outlet of gas turbine engines are described. The flow diverters include a diverter body having a connector portion defining a diverter inlet, a diverter extension at least partially defining a diverter outlet, and a curved portion arranged between the connector portion and the diverter extension, the curved portion configured to change a direction of flow from a first direction to a second direction that is about 90° from the first direction as the flow passes from the diverter inlet to the diverter outlet.Type: ApplicationFiled: January 22, 2021Publication date: August 12, 2021Inventors: John S. Tu, Robert Newman, Paul K. Sanchez, Jeffrey J. Lienau, John T. Ols, Prabaharan Manoharan, Venu Sambarapu, Rajendra Prasad Uppara Allabanda
-
Patent number: 11022144Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.Type: GrantFiled: March 22, 2019Date of Patent: June 1, 2021Assignee: Raytheon Technologies CorporationInventors: Matthew Andrew Hough, John S. Tu, Stephen C. Harmon, Paul F. Croteau, Russell B. Hanson, Joshua C. Rathgeb
-
Patent number: 10941669Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.Type: GrantFiled: December 21, 2018Date of Patent: March 9, 2021Assignee: Raytheon Technologies CorporationInventors: Matthew A. Hough, Russell B. Hanson, John S. Tu, Paul F. Croteau, Paul K. Sanchez, Stephen C. Harmon, Joshua C. Rathgeb
-
Publication number: 20200362762Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.Type: ApplicationFiled: May 15, 2019Publication date: November 19, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew Andrew Hough, John S. Tu, Stephen C. Harmon, Paul F. Croteau, Russell B. Hanson, Joshua C. Rathgeb
-
Publication number: 20200300103Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.Type: ApplicationFiled: March 22, 2019Publication date: September 24, 2020Inventors: Matthew Andrew Hough, John S. Tu, Stephen C. Harmon, Paul F. Croteau, Russell B. Hanson, Joshua C. Rathgeb
-
Patent number: 10746403Abstract: A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face. A plurality of cooling member arrays of the liner each include a first plurality of members that may be pins projecting outward from the cold face to conduct heat out of the liner. Each array is spaced between adjacent effusion holes and is symmetrically orientated about the respective centerline.Type: GrantFiled: November 12, 2015Date of Patent: August 18, 2020Assignee: Raytheon Technologies CorporationInventors: John S. Tu, Steven W. Burd
-
Publication number: 20200200028Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.Type: ApplicationFiled: December 21, 2018Publication date: June 25, 2020Inventors: Matthew A. Hough, Russell B. Hanson, John S. Tu, Paul F. Croteau, Paul K. Sanchez, Stephen C. Harmon, Joshua C. Rathgeb
-
Patent number: 10684014Abstract: A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.Type: GrantFiled: August 4, 2016Date of Patent: June 16, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Brian T. Hazel, Kaitlin M. Tomeo, Robert Selinsky, Jr., Aaron S. Butler, John S. Tu, William F. Werkheiser, Jessica L. Serra
-
Patent number: 10598382Abstract: A liner associated with an engine of an aircraft is described. The liner includes a panel and an array of projections configured to enhance a cooling of the panel and distributed on at least part of a first side of the panel that corresponds to a cold side of the panel.Type: GrantFiled: November 6, 2015Date of Patent: March 24, 2020Assignee: United Technologies CorporationInventors: John S. Tu, James B. Hoke, Monica Pacheco-Tougas, Alexander W. Williams
-
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: 10502095Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid-turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid-turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.Type: GrantFiled: November 1, 2016Date of Patent: December 10, 2019Assignee: United Technologies CorporationInventors: Paul K. Sanchez, Kalpendu J. Parekh, William A. Daniels, John S. Tu
-
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
-
Patent number: 10317080Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.Type: GrantFiled: December 3, 2014Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventors: John S. Tu, Jr., Timothy S. Snyder, James B. Hoke, James P. Bangerter, Dennis J. Duhamel, David A. Burns
-
Patent number: 10260750Abstract: 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.Type: GrantFiled: December 29, 2015Date of Patent: April 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John S. Tu, James B. Hoke, Jonathan Jeffery Eastwood, Kevin Joseph Low, Sean D. Bradshaw
-
Patent number: 10215411Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.Type: GrantFiled: March 7, 2016Date of Patent: February 26, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John S. Tu, James B. Hoke, David Kwoka, Jonathan Jeffery Eastwood
-
Patent number: 10107120Abstract: A mid-turbine frame (MTF) for a gas turbine engine includes an inner manifold directing air to a turbine rotor of the gas turbine engine. The MTF includes an outer MTF case and an inner MTF case. The inner manifold of the MTF is located in the inner case of the MTF.Type: GrantFiled: August 24, 2016Date of Patent: October 23, 2018Assignee: United Technologies CorporationInventors: Paul K. Sanchez, John S. Tu, Kalpendu J. Parekh, William A. Daniels