Patents by Inventor Alex J. Schneider
Alex J. Schneider 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: 11661852Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.Type: GrantFiled: February 7, 2020Date of Patent: May 30, 2023Assignee: Raytheon Technologies CorporationInventors: Nicholas M. LoRicco, Parth Jariwala, Alex J. Schneider, Bret M. Teller, Matthew S. Gleiner, Jeffrey T. Morton
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Patent number: 11536145Abstract: An airfoil vane assembly according to an exemplary embodiment of this disclosure, among other possible things includes a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform, a spar piece having a spar platform and a spar extending from the spar platform into the hollow airfoil section, and at least one seal arranged at a sealing surface of the spar platform and sealing between the spar platform and the first vane platform. The airfoil vane assembly also includes a thermal barrier coating disposed on the spar piece. The sealing surface is free from the thermal barrier coating. A gas turbine engine and a method of making a spar piece for an airfoil vane assembly are also disclosed.Type: GrantFiled: April 9, 2021Date of Patent: December 27, 2022Assignee: Raytheon Technologies CorporationInventors: San Quach, Alex J. Schneider
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Publication number: 20220325630Abstract: An airfoil vane assembly according to an exemplary embodiment of this disclosure, among other possible things includes a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform, a spar piece having a spar platform and a spar extending from the spar platform into the hollow airfoil section, and at least one seal arranged at a sealing surface of the spar platform and sealing between the spar platform and the first vane platform. The airfoil vane assembly also includes a thermal barrier coating disposed on the spar piece. The sealing surface is free from the thermal barrier coating. A gas turbine engine and a method of making a spar piece for an airfoil vane assembly are also disclosed.Type: ApplicationFiled: April 9, 2021Publication date: October 13, 2022Inventors: San Quach, Alex J. Schneider
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Patent number: 11346230Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.Type: GrantFiled: February 3, 2020Date of Patent: May 31, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Alex J. Schneider, Parth Jariwala, Nicholas M. LoRicco, Ryan Lundgreen, David A. Niezelski, Jeffrey T. Morton
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Publication number: 20220098988Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.Type: ApplicationFiled: February 7, 2020Publication date: March 31, 2022Applicant: Raytheon Technologies CorporationInventors: Nicholas M. LoRicco, Parth Jariwala, Alex J. Schneider, Bret M. Teller, Matthew S. Gleiner, Jeffrey T. Morton
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Patent number: 11215059Abstract: An airfoil includes a ceramic airfoil section that defines leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The span of the airfoil section has first, second, and third radial span zones. There is a row of cooling holes in an aft 25% of the axial span. The row of cooling holes extends though the first, second, and third radial span zones. The cooling holes in the first radial span zone define a first pitch P1, the cooling holes in the second radial span zone define a second pitch P2, and the cooling holes in the third radial span zone define a third pitch P3, wherein P2<P3<P1.Type: GrantFiled: September 3, 2020Date of Patent: January 4, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Bryan P. Dube, Raymond Surace, Alex J. Schneider, Tyler G. Vincent
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Patent number: 11208898Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.Type: GrantFiled: February 3, 2020Date of Patent: December 28, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Alex J. Schneider, Parth Jariwala, Nicholas M. LoRicco, Ryan Lundgreen, David A. Niezelski, Jeffrey T. Morton
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Patent number: 11143037Abstract: A turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes are located in an airfoil of the turbine blade according to the coordinates of Table 1.Type: GrantFiled: February 3, 2020Date of Patent: October 12, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Alex J. Schneider, Timothy J. Jennings, David A. Niezelski, Jeffrey T. Morton, Nicholas M. LoRicco, Bret M. Teller
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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: 11085304Abstract: A component for a gas turbine engine may comprise a cooling channel. A first trip strip may extend from a wall of the cooling channel. A leg of the first trip strip and a first plane orthogonal to a direction of airflow through the cooling channel may form a first angle. A second trip strip may be downstream from the first trip strip and extending from the wall of the cooling channel. A leg of the second trip strip and a second plane orthogonal to the direction of airflow through the cooling channel may form a second angle different from the first angle.Type: GrantFiled: June 7, 2018Date of Patent: August 10, 2021Assignee: Raytheon Technologies CorporationInventors: Jeremy Styborski, Alex J. Schneider
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Patent number: 11060408Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.Type: GrantFiled: February 3, 2020Date of Patent: July 13, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Alex J. Schneider, Parth Jariwala, Nicholas M. LoRicco, Ryan Lundgreen, David A. Niezelski, Jeffrey T. Morton
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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: 10871083Abstract: A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: HDA, HDB, HEA, HEB, SAA, SAB, and HCA of Table 1.Type: GrantFiled: March 23, 2018Date of Patent: December 22, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Christopher Cosher, Alex J. Schneider, Bret M. Teller
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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: 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: 20190376393Abstract: A component for a gas turbine engine may comprise a cooling channel. A first trip strip may extend from a wall of the cooling channel. A leg of the first trip strip and a first plane orthogonal to a direction of airflow through the cooling channel may form a first angle. A second trip strip may be downstream from the first trip strip and extending from the wall of the cooling channel. A leg of the second trip strip and a second plane orthogonal to the direction of airflow through the cooling channel may form a second angle different from the first angle.Type: ApplicationFiled: June 7, 2018Publication date: December 12, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jeremy Styborski, Alex J. Schneider
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Publication number: 20190292940Abstract: A turbine vane for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes provide fluid communication to a surface of the turbine vane, the plurality of cooling holes including holes noted by the following coordinates: HDA, HDB, HEA, HEB, SAA, SAB, and HCA of Table 1.Type: ApplicationFiled: March 23, 2018Publication date: September 26, 2019Inventors: Christopher Cosher, Alex J. Schneider, Bret M. Teller
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Patent number: 10104313Abstract: A method for evaluating a turbine component includes inducing a thermal response of the component at an initial time, capturing a two-dimensional infrared image of the thermal response of the component with a thermal imaging device, wherein the two-dimensional infrared image comprises a plurality of infrared image pixels, generating a two-dimension to three-dimension mapping template to correlate two-dimensional infrared image data with three-dimensional locations on the component, mapping at least a subset of the plurality of infrared image pixels of the two-dimensional infrared image to three-dimensional coordinates using the mapping template, and generating a three-dimensional infrared image and infrared data of the component from the mapped infrared image pixels to three-dimensional coordinates, wherein the three-dimensional infrared image and infrared data is used to qualify the component for use.Type: GrantFiled: July 8, 2016Date of Patent: October 16, 2018Assignee: United Technologies CorporationInventors: Thomas N. Slavens, Jeremy Styborski, Alex J. Schneider, Lea Kennard Castle, Rodney H. Warner, James Tilsley Auxier
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Publication number: 20180013959Abstract: A method for evaluating a turbine component includes inducing a thermal response of the component at an initial time, capturing a two-dimensional infrared image of the thermal response of the component with a thermal imaging device, wherein the two-dimensional infrared image comprises a plurality of infrared image pixels, generating a two-dimension to three-dimension mapping template to correlate two-dimensional infrared image data with three-dimensional locations on the component, mapping at least a subset of the plurality of infrared image pixels of the two-dimensional infrared image to three-dimensional coordinates using the mapping template, and generating a three-dimensional infrared image and infrared data of the component from the mapped infrared image pixels to three-dimensional coordinates, wherein the three-dimensional infrared image and infrared data is used to qualify the component for use.Type: ApplicationFiled: July 8, 2016Publication date: January 11, 2018Inventors: Thomas N. Slavens, Jeremy Styborski, Alex J. Schneider, Lea Kennard Castle, Rodney H. Warner, James Tilsley Auxier