Patents by Inventor Joseph Anthony Weber
Joseph Anthony Weber 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: 11339666Abstract: An article, such as a turbine blade, includes an airfoil. The airfoil includes a body, the body having an elongated internal cavity extending from a tip of the body. The cavity is defined an internal wall within the body. At least one elongated damping element is disposed in the elongated internal cavity and frictionally engages the internal wall. Thus, the least one elongated damping element is capable of damping vibrations in the article.Type: GrantFiled: April 17, 2020Date of Patent: May 24, 2022Assignee: General Electric CompanyInventors: Andrew Clifford Hart, John McConnell Delvaux, Joseph Anthony Weber, James Zhang, Peter de Diego
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Publication number: 20210324743Abstract: An article, such as a turbine blade, includes an airfoil. The airfoil includes a body, the body having an elongated internal cavity extending from a tip of the body. The cavity is defined an internal wall within the body. At least one elongated damping element is disposed in the elongated internal cavity and frictionally engages the internal wall. Thus, the least one elongated damping element is capable of damping vibrations in the article.Type: ApplicationFiled: April 17, 2020Publication date: October 21, 2021Inventors: Andrew Clifford Hart, John McConnell Delvaux, Joseph Anthony Weber, James Zhang, Peter de Diego
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Patent number: 10989070Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.Type: GrantFiled: May 31, 2018Date of Patent: April 27, 2021Assignee: General Electric CompanyInventors: Brad Wilson VanTassel, Evan Andrew Sewall, Joseph Anthony Weber, Travis J Packer, Joseph Daniel Franzen, Jr., Bryan David Lewis
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Patent number: 10851663Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a passage extending from a root to a tip of the airfoil. The passage includes a first passage portion and a second passage portion. The first passage portion has a greater diameter than the second passage portion. The rotor blade also includes a first tube positioned within the first passage portion. The first tube is spaced apart from the airfoil. The rotor blade further includes a second tube positioned within the first passage portion. The second tube is positioned between the airfoil and the first tube. Furthermore, the rotor blade includes a plurality of inserts positioned within the first passage portion. The plurality of inserts is positioned between and in contact with the first and second tubes.Type: GrantFiled: June 12, 2017Date of Patent: December 1, 2020Assignee: General Electric CompanyInventors: Sandip Dutta, Joseph Anthony Weber
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Patent number: 10815807Abstract: A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments circumferentially stacked about a hot gas path. The inner shroud segments may include a first inner shroud segment that includes: a cooling configuration having cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, where each of the cooling channels extends lengthwise between a first end and a second end that includes an outlet formed through an exterior surface of the first inner shroud segment; a circumferential edge; a slot formed in the circumferential edge; and a sealing member positioned within the slot. The outlet of at least one of the cooling channels may be positioned within the slot.Type: GrantFiled: May 31, 2018Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Brad Wilson VanTassel, Steven Paul Byam, Joseph Anthony Weber, Evan Andrew Sewall, Travis J Packer
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Patent number: 10774683Abstract: A fixture for drilling a hole in a superalloy turbine blade includes a mount to selectively hold a root of the superalloy turbine blade with the superalloy turbine blade extending from the mount. The fixture may also include an actuator to apply a force to elastically deform at least a portion of the superalloy turbine blade when held by the mount from a relaxed, initial position to an elastically deformed position, the at least a portion of the superalloy turbine blade having a curvature in the elastically deformed position not present in the relaxed, initial position. The fixture may also include a drill guide configured to guide a drilling element into the superalloy turbine blade in the elastically deformed position.Type: GrantFiled: April 12, 2017Date of Patent: September 15, 2020Assignee: General Electric CompanyInventors: Robert Frank Hoskin, Robert Aldo Del Freo, Joseph William Janssen, Joseph Leonard Moroso, Eric Alan Overholt, Matthew Ian Van Biervliet, Joseph Anthony Weber
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Patent number: 10767501Abstract: An article, a component, and a method of making a component are provided. The article includes a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component. The component includes a first end wall, a second end wall, and an article including a contoured proximal face secured to at least one of the first end wall and the second end wall. The method of making a component includes forming an article having a proximal face and a distal face, contouring the proximal face of the article to form a contoured proximal face that substantially mirrors a contour of a first end wall or a second end wall of the component, and securing the contoured proximal face of the article to one of the first end wall and the second end wall.Type: GrantFiled: April 21, 2016Date of Patent: September 8, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Joseph Anthony Weber, Srikanth Chandrudu Kottilingam, Brian Lee Tollison
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Patent number: 10738651Abstract: A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.Type: GrantFiled: May 31, 2018Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: Brad Wilson VanTassel, Joseph Anthony Weber, Bryan David Lewis, Travis J Packer
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Patent number: 10655477Abstract: Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.Type: GrantFiled: July 26, 2016Date of Patent: May 19, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Sandip Dutta, Benjamin Paul Lacy, Gary Michael Itzel, Joseph Anthony Weber, David Edward Schick
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Publication number: 20190368378Abstract: A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.Type: ApplicationFiled: May 31, 2018Publication date: December 5, 2019Applicant: General Electric CompanyInventors: Brad Wilson VanTassel, Joseph Anthony Weber, Bryan David Lewis, Travis J Packer
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Publication number: 20190368377Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.Type: ApplicationFiled: May 31, 2018Publication date: December 5, 2019Applicant: General Electric CompanyInventors: Brad Wilson VanTassel, Evan Andrew Sewall, Joseph Anthony Weber, Travis J Packer, Joseph Daniel Franzen, JR., Bryan David Lewis
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Publication number: 20190368364Abstract: A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments circumferentially stacked about a hot gas path. The inner shroud segments may include a first inner shroud segment that includes: a cooling configuration having cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, where each of the cooling channels extends lengthwise between a first end and a second end that includes an outlet formed through an exterior surface of the first inner shroud segment; a circumferential edge; a slot formed in the circumferential edge; and a sealing member positioned within the slot. The outlet of at least one of the cooling channels may be positioned within the slot.Type: ApplicationFiled: May 31, 2018Publication date: December 5, 2019Applicant: General Electric CompanyInventors: Brad Wilson VanTassel, Steven Paul Byam, Joseph Anthony Weber, Evan Andrew Sewall, Travis J. Packer
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Patent number: 10494948Abstract: An airfoil including a leading edge, a trailing edge, a pressure side, a suction side, and an internal impingement cavity. An impingement insert is located within the impingement cavity. The impingement insert includes at least one impingement cooling hole spaced along a first face of the impingement insert and at least one impingement fin, having a base and a tip opposite the base, spaced along the first face of the impingement insert. The at least one impingement fin is spaced apart from the at least one impingement cooling hole.Type: GrantFiled: May 9, 2017Date of Patent: December 3, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Sandip Dutta, Joseph Anthony Weber, Benjamin Paul Lacy
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Patent number: 10392945Abstract: The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.Type: GrantFiled: May 19, 2017Date of Patent: August 27, 2019Assignee: General Electric CompanyInventors: Sandip Dutta, Scott Francis Johnson, Joseph Anthony Weber
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Patent number: 10233761Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.Type: GrantFiled: October 26, 2016Date of Patent: March 19, 2019Assignee: General Electric CompanyInventors: Zachary John Snider, Gregory Thomas Foster, Joseph Anthony Weber, James Fredric Wiedenhoefer
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Patent number: 10220461Abstract: A method includes applying a force to elastically deform at least a portion of a superalloy turbine blade from a relaxed, initial position to an elastically deformed position. The at least a portion of the superalloy turbine blade has a curvature in the elastically deformed position not present in the relaxed, initial position. A hole is drilled generally span-wise through the at least a portion of the superalloy turbine blade in the elastically deformed position, and when the force is released, the superalloy turbine blade returns to the relaxed, initial position and the hole takes on a hole curvature within the at least a portion of the superalloy turbine blade.Type: GrantFiled: April 12, 2017Date of Patent: March 5, 2019Assignee: General Electric CompanyInventors: Robert Frank Hoskin, Robert Aldo Del Freo, Joseph William Janssen, Joseph Leonard Moroso, Eric Alan Overholt, Matthew Ian Van Biervliet, Joseph Anthony Weber
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Publication number: 20190017392Abstract: The present disclosure is directed to an impingement insert for a turbomachine. The impingement insert includes an insert body having an inner surface, an outer surface spaced apart from the inner surface, and a thickness extending from the inner surface to the outer surface. The insert body defines a first depression extending from one of the inner surface or the outer surface into the insert body. The first depression has a diameter. The insert body further defines an impingement aperture extending from the first depression through the insert body. The impingement aperture has a length and a diameter. The thickness of the insert body is greater than the length of the impingement aperture and the diameter of the first depression is greater than the diameter of the impingement aperture.Type: ApplicationFiled: July 13, 2017Publication date: January 17, 2019Inventors: Sandip Dutta, Kassy Moy Hart, Joseph Anthony Weber, Sean Patrick Gunning
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Publication number: 20180355730Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a passage extending from a root to a tip of the airfoil. The passage includes a first passage portion and a second passage portion. The first passage portion has a greater diameter than the second passage portion. The rotor blade also includes a first tube positioned within the first passage portion. The first tube is spaced apart from the airfoil. The rotor blade further includes a second tube positioned within the first passage portion. The second tube is positioned between the airfoil and the first tube. Furthermore, the rotor blade includes a plurality of inserts positioned within the first passage portion. The plurality of inserts is positioned between and in contact with the first and second tubes.Type: ApplicationFiled: June 12, 2017Publication date: December 13, 2018Inventors: Sandip Dutta, Joseph Anthony Weber
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Publication number: 20180334910Abstract: The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.Type: ApplicationFiled: May 19, 2017Publication date: November 22, 2018Inventors: Sandip Dutta, Scott Francis Johnson, Joseph Anthony Weber
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Publication number: 20180328224Abstract: An airfoil including a leading edge, a trailing edge, a pressure side, a suction side, and an internal impingement cavity. An impingement insert is located within the impingement cavity. The impingement insert includes at least one impingement cooling hole spaced along a first face of the impingement insert and at least one impingement fin, having a base and a tip opposite the base, spaced along the first face of the impingement insert. The at least one impingement fin is spaced apart from the at least one impingement cooling hole.Type: ApplicationFiled: May 9, 2017Publication date: November 15, 2018Inventors: Sandip DUTTA, Joseph Anthony WEBER, Benjamin Paul LACY