Patents by Inventor James Michael Hoffman
James Michael Hoffman 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: 11814186Abstract: In a jet engine having a core that sources a first flow of fluid and a component (such as a fan, a pump, and/or a bleed line) that sources a second flow of fluid, and where the first flow of fluid will typically have, at least during ordinary operation, a higher temperature than the second flow of fluid, at least one flow aperture formed by a first passageway to receive at least a portion of the aforementioned second flow of fluid, wherein that first passageway is comprised of at least one material that (by design and intent) deflects as a function of temperature such that a flow of the second flow of fluid through the at least one flow aperture is thereby desirably modulated.Type: GrantFiled: December 8, 2021Date of Patent: November 14, 2023Assignee: General Electric CompanyInventors: James Michael Hoffman, Michael G. Chenery, David A. Perveiler, Dennis R. Jonassen, Scott Alan Schimmels
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Publication number: 20230174246Abstract: In a jet engine having a core that sources a first flow of fluid and a component (such as a fan, a pump, and/or a bleed line) that sources a second flow of fluid, and where the first flow of fluid will typically have, at least during ordinary operation, a higher temperature than the second flow of fluid, at least one flow aperture formed by a first passageway to receive at least a portion of the aforementioned second flow of fluid, wherein that first passageway is comprised of at least one material that (by design and intent) deflects as a function of temperature such that a flow of the second flow of fluid through the at least one flow aperture is thereby desirably modulated.Type: ApplicationFiled: December 8, 2021Publication date: June 8, 2023Inventors: James Michael Hoffman, Michael G. Chenery, David A. Perveiler, Dennis R. Jonassen, Scott Alan Schimmels
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Publication number: 20220356805Abstract: An airfoil assembly for a gas turbine engine having a core with a working airflow. The airfoil assembly comprising a dovetail, a platform, an airfoil, a fluid circuit and at least one curvilinear cooling passage. The platform extending from the dovetail and having an outer surface confronting the working airflow. The at least one curvilinear fluid passage extending between an inlet in direct fluid communication with the fluid circuit and an outlet on the outer surface.Type: ApplicationFiled: July 14, 2022Publication date: November 10, 2022Inventors: James Michael Hoffman, Danielle Leigh Polizzi
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Patent number: 11401817Abstract: An airfoil assembly for a gas turbine engine including a blade, platform, and dovetail. The airfoil assembly further includes a cooling circuit including an interior chamber of the dovetail having fluid communication with the exterior of the airfoil assembly or with an interior chamber of the blade and at least one cooling passage.Type: GrantFiled: November 4, 2016Date of Patent: August 2, 2022Assignee: General Electric CompanyInventors: James Michael Hoffman, Danielle Leigh Polizzi
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Patent number: 10941671Abstract: A turbine engine component includes: a body bounded by an end face; and a seal slot having an opening communicating with the end face, the seal slot including a receptacle defining a boundary configured to receive and position a spline seal, and an open chamber communicating with the seal slot and extending beyond the boundary.Type: GrantFiled: March 23, 2017Date of Patent: March 9, 2021Assignee: General Electric CompanyInventors: Weston Nolan Dooley, James Michael Hoffman, Gregory Terrence Garay
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Patent number: 10808572Abstract: A gas turbine engine that includes a turbomachinery core operable to produce a core gas flow and that includes a combustor. A first duct is positioned downstream of and in flow communication with the combustor. A component is positioned within the first duct and extends between radially outward and radially inward walls of the first duct. The component that includes a first cooling passageway formed therein. The first cooling passageway extends between an inlet communicating with the first duct and positioned facing towards the turbomachinery core, and an outlet communicating with a pressure sink.Type: GrantFiled: April 2, 2018Date of Patent: October 20, 2020Assignee: General Electric CompanyInventors: James Michael Hoffman, Jeffrey Ryan Trimmer, Dennis Robert Jonassen, Mark Stephen Zlatic, Patrick John Lonneman
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Patent number: 10697301Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.Type: GrantFiled: April 7, 2017Date of Patent: June 30, 2020Assignee: General Electric CompanyInventors: James Michael Hoffman, Weston Nolan Dooley, Matthew Lee Krumanaker, Aaron Ezekiel Smith, Steven Robert Brassfield
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Patent number: 10508548Abstract: An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.Type: GrantFiled: April 7, 2017Date of Patent: December 17, 2019Assignee: General Electric CompanyInventors: James Michael Hoffman, Weston Nolan Dooley, Aaron Ezekiel Smith, Steven Robert Brassfield
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Patent number: 10443400Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior and spanning from a root to a tip. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define an air flow channel within the airfoil. The air flow channel can have at least one tip turn at the partial-length rib, having at least one hole, for example a film hole, in a portion of the tip.Type: GrantFiled: August 16, 2016Date of Patent: October 15, 2019Assignee: General Electric CompanyInventor: James Michael Hoffman
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Patent number: 10443403Abstract: An apparatus relating to engineering the geometry for a ball-chute support feature in an investment casting core. The investment casting core is for an airfoil region having at least one serpentine feature and at least one inlet feature coupled to the at least one serpentine feature by a ball-chute support feature. The investment casting core is leached out to form cooling passages in the airfoil.Type: GrantFiled: January 23, 2017Date of Patent: October 15, 2019Assignee: General Electric CompanyInventors: Weston Nolan Dooley, James Michael Hoffman, Steven Robert Brassfield
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Publication number: 20190301301Abstract: A gas turbine engine that includes a turbomachinery core operable to produce a core gas flow and that includes a combustor. A first duct is positioned downstream of and in flow communication with the combustor. A component is positioned within the first duct and extends between radially outward and radially inward walls of the first duct. The component that includes a first cooling passageway formed therein. The first cooling passageway extends between an inlet communicating with the first duct and positioned facing towards the turbomachinery core, and an outlet communicating with a pressure sink.Type: ApplicationFiled: April 2, 2018Publication date: October 3, 2019Inventors: James Michael Hoffman, Jeffrey Ryan Trimmer, Dennis Robert Jonassen, Mark Stephen Zlatic, Patrick John Lonneman
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Publication number: 20180320530Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.Type: ApplicationFiled: May 5, 2017Publication date: November 8, 2018Inventors: Kevin Robert Feldmann, Robert Charles Groves, II, Weston Nolan Dooley, James Michael Hoffman
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Publication number: 20180291743Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.Type: ApplicationFiled: April 7, 2017Publication date: October 11, 2018Inventors: James Michael Hoffman, Weston Nolan Dooley, Matthew Lee Krumanaker, Aaron Ezekiel Smith, Steven Robert Brassfield
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Publication number: 20180291742Abstract: An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.Type: ApplicationFiled: April 7, 2017Publication date: October 11, 2018Inventors: James Michael Hoffman, Weston Nolan Dooley, Aaron Ezekiel Smith, Steven Robert Brassfield
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Publication number: 20180274381Abstract: A turbine engine component includes: a body bounded by an end face; and a seal slot having an opening communicating with the end face, the seal slot including a receptacle defining a boundary configured to receive and position a spline seal, and an open chamber communicating with the seal slot and extending beyond the boundary.Type: ApplicationFiled: March 23, 2017Publication date: September 27, 2018Inventors: Weston Nolan Dooley, James Michael Hoffman, Gregory Terrence Garay
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Publication number: 20180209277Abstract: An apparatus relating to engineering the geometry for a ball-chute support feature in an investment casting core. The investment casting core is for an airfoil region having at least one serpentine feature and at least one inlet feature coupled to the at least one serpentine feature by a ball-chute support feature. The investment casting core is leached out to form cooling passages in the airfoil.Type: ApplicationFiled: January 23, 2017Publication date: July 26, 2018Inventors: Weston Nolan Dooley, James Michael Hoffman, Steven Robert Brassfield
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Publication number: 20180128113Abstract: An airfoil assembly for a gas turbine engine including a blade, platform, and dovetail. The airfoil assembly further includes a cooling circuit including an interior chamber of the dovetail having fluid communication with the exterior of the airfoil assembly or with an interior chamber of the blade and at least one cooling passage.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: James Michael Hoffman, Danielle Leigh Polizzi
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Publication number: 20180051572Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior and spanning from a root to a tip. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define an air flow channel within the airfoil. The air flow channel can have at least one tip turn at the partial-length rib, having at least one hole, for example a film hole, in a portion of the tip.Type: ApplicationFiled: August 16, 2016Publication date: February 22, 2018Inventor: James Michael Hoffman