Patents by Inventor Noah Wadsworth
Noah Wadsworth 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: 11041391Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.Type: GrantFiled: April 20, 2020Date of Patent: June 22, 2021Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
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Patent number: 11015464Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: GrantFiled: January 24, 2020Date of Patent: May 25, 2021Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Publication number: 20200386106Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.Type: ApplicationFiled: April 20, 2020Publication date: December 10, 2020Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
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Publication number: 20200277867Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: ApplicationFiled: January 24, 2020Publication date: September 3, 2020Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10738701Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.Type: GrantFiled: August 30, 2017Date of Patent: August 11, 2020Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10584601Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: GrantFiled: August 30, 2017Date of Patent: March 10, 2020Assignee: United Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10415401Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.Type: GrantFiled: September 8, 2016Date of Patent: September 17, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Noah Wadsworth, Elizabeth F. Vinson
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Patent number: 10392966Abstract: A gas turbine engine and a retaining ring are disclosed. The gas turbine engine includes a rotating disc assembly, including a rotating disc, a cover plate, and a retaining ring disposed between the rotating disc and the cover plate, wherein the retaining ring axially retains the rotating disc and the cover plate, the retaining ring including a rotating disc face to interface with the rotating disc; a cover plate face to interface with the cover plate; and an end gap portion defining an end gap, wherein at least one of the rotating disc face, the cover plate face, and the end gap portion includes a stress reducing feature.Type: GrantFiled: September 23, 2016Date of Patent: August 27, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Joseph T. Caprario, Noah Wadsworth, Mark E. Marler, James P. Allore, Elizabeth F. Vinson
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Publication number: 20190063239Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Publication number: 20190063323Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Publication number: 20180087397Abstract: A gas turbine engine and a retaining ring are disclosed. The gas turbine engine includes a rotating disc assembly, including a rotating disc, a cover plate, and a retaining ring disposed between the rotating disc and the cover plate, wherein the retaining ring axially retains the rotating disc and the cover plate, the retaining ring including a rotating disc face to interface with the rotating disc; a cover plate face to interface with the cover plate; and an end gap portion defining an end gap, wherein at least one of the rotating disc face, the cover plate face, and the end gap portion includes a stress reducing feature.Type: ApplicationFiled: September 23, 2016Publication date: March 29, 2018Inventors: Joseph T. Caprario, Noah Wadsworth, Mark E. Marler, James P. Allore, Elizabeth F. Vinson
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Publication number: 20180066529Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.Type: ApplicationFiled: September 8, 2016Publication date: March 8, 2018Inventors: Noah Wadsworth, Elizabeth F. Vinson