Patents by Inventor Shawn M. McMahon
Shawn M. McMahon 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: 11187092Abstract: A vane for a gas turbine engine, the vane having: an airfoil; and a root portion disposed on a side of the airfoil and including a platform, the platform having a vane forward rail and an extension extending from the platform, the extension defining portions of an outer diameter platform cavity and an airfoil leading edge cavity. The extension extends from the platform such that an upper portion of each of the outer diameter platform cavity and the airfoil leading edge cavity is spaced equidistant from the platform.Type: GrantFiled: May 17, 2019Date of Patent: November 30, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Shawn M. McMahon, Nicholas J. Madonna
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Patent number: 11111794Abstract: A seal assembly includes a first feather seal with a first cooling hole extending through the first feather seal. The seal assembly also includes a second feather seal adjacent to the first feather seal. The second feather seal includes a second cooling hole extending through the second feather seal. The first cooling hole is positioned over at least a portion of the second cooling hole.Type: GrantFiled: February 5, 2019Date of Patent: September 7, 2021Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: David Bitzko, Shawn M. McMahon, Alex J. Schneider
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Patent number: 11078796Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.Type: GrantFiled: December 14, 2018Date of Patent: August 3, 2021Assignee: Raytheon Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
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Patent number: 11073024Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: GrantFiled: December 14, 2018Date of Patent: July 27, 2021Assignee: Raytheon Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Mohamed Hassan, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher
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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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Patent number: 11008872Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: GrantFiled: December 14, 2018Date of Patent: May 18, 2021Assignee: Raytheon Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
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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: 20200362711Abstract: A vane for a gas turbine engine, the vane having: an airfoil; and a root portion disposed on a side of the airfoil and including a platform, the platform having a vane forward rail and an extension extending from the platform, the extension defining portions of an outer diameter platform cavity and an airfoil leading edge cavity. The extension extends from the platform such that an upper portion of each of the outer diameter platform cavity and the airfoil leading edge cavity is spaced equidistant from the platform.Type: ApplicationFiled: May 17, 2019Publication date: November 19, 2020Inventors: Shawn M. McMahon, Nicholas J. Madonna
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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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Publication number: 20200248566Abstract: A seal assembly includes a first feather seal with a first cooling hole extending through the first feather seal. The seal assembly also includes a second feather seal adjacent to the first feather seal. The second feather seal includes a second cooling hole extending through the second feather seal. The first cooling hole is positioned over at least a portion of the second cooling hole.Type: ApplicationFiled: February 5, 2019Publication date: August 6, 2020Inventors: David Bitzko, Shawn M. McMahon, Alex J. Schneider
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Publication number: 20200190993Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: United Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Mohamed Hassan, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher
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Publication number: 20200190995Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: United Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
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Publication number: 20200190994Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: United Technologies CorporationInventors: Christopher Perron, Justin M. Aniello, Shawn M. McMahon, Ricardo Trindade, Steven Bruce Gautschi, David Barger, Brett Alan Bartling, Nicholas J. Madonna, Robin Prenter, Ryan Lundgreen, Christopher Cosher, Mohamed Hassan
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Patent number: 10648363Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.Type: GrantFiled: December 28, 2017Date of Patent: May 12, 2020Assignee: United Technologies CorporationInventors: Shawn M. McMahon, Christopher Whitfield, Nicholas M. LoRicco, Steven Bruce Gautschi, Vincent E. Simms, Justin M. Aniello, Thomas Allwood, Richard M. Salzillo, Jeffery Scott Hembree, Sr.
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Patent number: 10641102Abstract: A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.Type: GrantFiled: October 23, 2017Date of Patent: May 5, 2020Assignee: United Technologies CorporationInventors: Shawn M. McMahon, Christopher Whitfield, Kristopher K. Anderson, Jason B. Moran, Brett Alan Bartling, Christopher Perron, Justin M. Aniello, Stephanie Tanner, Dominic J. Mongillo, Jr.
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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: 10533425Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.Type: GrantFiled: December 28, 2017Date of Patent: January 14, 2020Assignee: United Technologies CorporationInventors: Shawn M. McMahon, Christopher Whitfield, Nicholas M. LoRicco, Steven Bruce Gautschi, Vincent E. Simms, Justin M. Aniello, Thomas Allwood, Richard M. Salzillo, Jeffery Scott Hembree, Sr.
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Patent number: 10502079Abstract: A seal segment includes a flapper seal, a wire mesh acting as a hinge for the flapper seal, and a spring. The flapper seal has a first surface and a second surface. The wire mesh includes a first section connected to the first surface of the flapper seal and a second section connected to the first section. The spring includes a first end that is in contact with the first section of the wire mesh to apply pressure to the first surface of the flapper seal and a second end adjacent the second section of the wire mesh.Type: GrantFiled: October 27, 2017Date of Patent: December 10, 2019Assignee: United Technologies CorporationInventors: Witt C. Guinn, Shawn M. McMahon