Patents by Inventor Seth A. Max
Seth A. Max 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).
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Patent number: 10598381Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis. A combustor of a gas turbine engine includes a bulkhead support shell with a swirler boss. The combustor also includes a swirler mountable to the swirler boss at a threaded interface defined around a swirler central longitudinal axis.Type: GrantFiled: May 15, 2014Date of Patent: March 24, 2020Assignee: United Technologies CorporationInventors: Christopher Drake, Seth A. Max, Meggan Harris
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Patent number: 10473330Abstract: 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.Type: GrantFiled: November 18, 2014Date of Patent: November 12, 2019Assignee: United Technologies CorporationInventors: Seth A. Max, Kevin J. Low
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Patent number: 10436449Abstract: The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.Type: GrantFiled: September 16, 2016Date of Patent: October 8, 2019Assignee: United Technologies CorporationInventors: Seth A. Max, Jonathan M. Jause
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Patent number: 10215098Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.Type: GrantFiled: January 22, 2015Date of Patent: February 26, 2019Assignee: United Technologies CorporationInventors: Anthony P. Cherolis, Jorge I. Farah, Seth A. Max, John H. Mosley, Steven D. Porter, Gregory E. Reinhardt, Kevin Zacchera
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Patent number: 10161256Abstract: A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.Type: GrantFiled: January 22, 2015Date of Patent: December 25, 2018Assignee: Untied Technologies CorporationInventors: Steven D. Porter, Seth A. Max
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Patent number: 10107141Abstract: The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a first circumferential seal, a second circumferential seal and a seal support structure configured to retain at least a portion of each of the first and second seals. The seal support structure is mounted between a turbine assembly and bearing compartment, and wherein the first and second seals provide barriers to a cavity between the turbine assembly and bearing compartment.Type: GrantFiled: April 13, 2015Date of Patent: October 23, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Seth A. Max, Anthony P. Cherolis
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Patent number: 10101031Abstract: A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.Type: GrantFiled: June 30, 2014Date of Patent: October 16, 2018Assignee: United Technologies CorporationInventors: Alexander W. Williams, Seth A. Max, Christopher B. Lyons
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Patent number: 10088166Abstract: A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward. The multiple of circumferentially arranged tabs are radially displaced from the threaded section.Type: GrantFiled: May 15, 2014Date of Patent: October 2, 2018Assignee: United Technologies CorporationInventors: Christopher Drake, Seth A. Max, Meggan Harris
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Patent number: 9828881Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.Type: GrantFiled: March 19, 2015Date of Patent: November 28, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Seth A. Max, Anthony P. Cherolis, Steven D. Porter, Joshua D. Winn, Gregory E. Reinhardt, Jeffrey J. Lienau
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Patent number: 9822666Abstract: A washer includes a first lobe comprising a first hole, a second lobe comprising a second hole, a third lobe comprising a third hole, and a fourth lobe comprising a fourth hole. A first leg extends from the first lobe to the second lobe, and a second leg extends between the third lobe and the fourth lobe, wherein the second leg is parallel to the first leg. A third leg extends from the first lobe to the third lobe and spaces the first leg from the second leg such that the second lobe is disposed opposite the fourth lobe.Type: GrantFiled: April 6, 2015Date of Patent: November 21, 2017Assignee: United Technologies CorporationInventors: Seth A. Max, Steven D. Porter
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Patent number: 9822667Abstract: A washer includes a hub and a first lobe connected to the hub. The first lobe includes a first hole. A second lobe is also connected to the hub and includes a second hole. A third lobe is also connected to the hub and includes a third hole. The first lobe extends from the hub at least partially in a first direction opposite the second lobe and the third lobe.Type: GrantFiled: April 6, 2015Date of Patent: November 21, 2017Assignee: United Technologies CorporationInventors: Steven D. Porter, Anthony P. Cherolis, Alberto A. Mateo, Joshua Daniel Winn, Seth A. Max
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Publication number: 20170227226Abstract: The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.Type: ApplicationFiled: September 16, 2016Publication date: August 10, 2017Inventors: Seth A. Max, Jonathan M. Jause
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Publication number: 20160376925Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.Type: ApplicationFiled: March 19, 2015Publication date: December 29, 2016Inventors: Seth A. Max, Anthony P. Cherolis, Steven D. Porter, Joshua D. Winn, Gregory E. Reinhardt, Jeffrey J. Lienau
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Publication number: 20160298473Abstract: The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a first circumferential seal, a second circumferential seal and a seal support structure configured to retain at least a portion of each of the first and second seals. The seal support structure is mounted between a turbine assembly and bearing compartment, and wherein the first and second seals provide barriers to a cavity between the turbine assembly and bearing compartment.Type: ApplicationFiled: April 13, 2015Publication date: October 13, 2016Inventors: Seth A. MAX, Anthony P. CHEROLIS
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Publication number: 20160290166Abstract: A washer includes a first lobe comprising a first hole, a second lobe comprising a second hole, a third lobe comprising a third hole, and a fourth lobe comprising a fourth hole. A first leg extends from the first lobe to the second lobe, and a second leg extends between the third lobe and the fourth lobe, wherein the second leg is parallel to the first leg. A third leg extends from the first lobe to the third lobe and spaces the first leg from the second leg such that the second lobe is disposed opposite the fourth lobe.Type: ApplicationFiled: April 6, 2015Publication date: October 6, 2016Inventors: Seth A. Max, Steven D. Porter
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Publication number: 20160290167Abstract: A washer includes a hub and a first lobe connected to the hub. The first lobe includes a first hole. A second lobe is also connected to the hub and includes a second hole. A third lobe is also connected to the hub and includes a third hole. The first lobe extends from the hub at least partially in a first direction opposite the second lobe and the third lobe.Type: ApplicationFiled: April 6, 2015Publication date: October 6, 2016Inventors: Steven D. Porter, Anthony P. Cherolis, Alberto A. Mateo, Joshua Daniel Winn, Seth A. Max
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Patent number: 9447974Abstract: The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirl assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.Type: GrantFiled: September 13, 2012Date of Patent: September 20, 2016Assignee: United Technologies CorporationInventors: Seth A. Max, Jonathan M. Jause
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Publication number: 20160265771Abstract: 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.Type: ApplicationFiled: November 18, 2014Publication date: September 15, 2016Inventors: Seth A. MAX, Kevin J. LOW
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Publication number: 20160215638Abstract: A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.Type: ApplicationFiled: January 22, 2015Publication date: July 28, 2016Inventors: Steven D. Porter, Seth A. Max
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Publication number: 20160215702Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.Type: ApplicationFiled: January 22, 2015Publication date: July 28, 2016Inventors: Anthony P. Cherolis, Jorge I. Farah, Seth A. Max, John H. Mosley, Steven D. Porter, Gregory E. Reinhardt, Kevin Zacchera