Patents by Inventor Anthony A. Weber
Anthony A. 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: 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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Publication number: 20190175366Abstract: In a powered actuator for supplying torque, joint equilibrium, and/or impedance to a joint, a motor is directly coupled to a low-reduction ratio transmission, e.g., a transmission having a gear ratio less than about 80 to 1. The motor has a low dissipation constant, e.g., less than about 50 W/(Nm)2. The transmission is serially connected to an elastic element that is also coupled to the joint, thereby supplying torque, joint equilibrium, and/or impedance to the joint while minimizing the power consumption and/or acoustic noise of the actuator.Type: ApplicationFiled: November 2, 2018Publication date: June 13, 2019Inventors: Hugh Miller Herr, Jeff Anthony Weber, Richard James Casler, JR.
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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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Patent number: 10143570Abstract: In a powered actuator for supplying torque, joint equilibrium, and/or impedance to a joint, a motor is directly coupled to a low-reduction ratio transmission, e.g., a transmission having a gear ratio less than about 80 to 1. The motor has a low dissipation constant, e.g., less than about 50 W/(Nm)2. The transmission is serially connected to an elastic element that is also coupled to the joint, thereby supplying torque, joint equilibrium, and/or impedance to the joint while minimizing the power consumption and/or acoustic noise of the actuator.Type: GrantFiled: January 23, 2018Date of Patent: December 4, 2018Assignee: Bionx Medical Technologies, Inc.Inventors: Hugh Miller Herr, Jeff Anthony Weber, Richard James Casler, Jr.
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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
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Patent number: 10119405Abstract: A cooling system according to an embodiment includes: a forked passage cooling circuit, the forked passage cooling circuit including a first leg and a second leg; and an air feed cavity for supplying cooling air to the first leg and the second leg of the forked passage cooling circuit; wherein the first leg of the forked passage cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the forked passage cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels in the multi-wall blade.Type: GrantFiled: December 21, 2015Date of Patent: November 6, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: David Wayne Weber, Brendon James Leary, Jacob Charles Perry, II, Joseph Anthony Weber
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Publication number: 20180297136Abstract: 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: ApplicationFiled: April 12, 2017Publication date: October 18, 2018Inventors: 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: 20180297137Abstract: 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: ApplicationFiled: April 12, 2017Publication date: October 18, 2018Inventors: 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: 10053989Abstract: A cooling system according to an embodiment includes: a pin fin bank cooling circuit; and an air feed cavity for supplying cooling air to the pin fin bank cooling circuit; wherein the pin fin bank cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade and a first set of near wall cooling channels of the multi-wall blade.Type: GrantFiled: December 21, 2015Date of Patent: August 21, 2018Assignee: General Electric CompanyInventors: David Wayne Weber, Gregory Thomas Foster, Gary Michael Itzel, Brendon James Leary, Joseph Anthony Weber
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Patent number: 10052683Abstract: A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.Type: GrantFiled: December 21, 2015Date of Patent: August 21, 2018Assignee: General Electric CompanyInventors: Gregory Thomas Foster, David Wayne Weber, Michelle Jessica Iduate, Brendon James Leary, Joseph Anthony Weber
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Patent number: 10030537Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define outer flow boundaries of the turbine nozzle. The inner band includes a gas side surface that is at least partially covered by one or more inner plates. The inner band also includes a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates. The outer band includes a gas side surface that is at least partially covered by one or more outer plates. The outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.Type: GrantFiled: October 12, 2015Date of Patent: July 24, 2018Assignee: General Electric CompanyInventors: Sandip Dutta, Benjamin Paul Lacy, Joseph Anthony Weber, Peter Galen Stevens
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Publication number: 20180153713Abstract: In a powered actuator for supplying torque, joint equilibrium, and/or impedance to a joint, a motor is directly coupled to a low-reduction ratio transmission, e.g., a transmission having a gear ratio less than about 80 to 1. The motor has a low dissipation constant, e.g., less than about 50 W/(Nm)2. The transmission is serially connected to an elastic element that is also coupled to the joint, thereby supplying torque, joint equilibrium, and/or impedance to the joint while minimizing the power consumption and/or acoustic noise of the actuator.Type: ApplicationFiled: January 23, 2018Publication date: June 7, 2018Inventors: Hugh Miller Herr, Jeff Anthony Weber, Richard James Casler, JR.
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Publication number: 20180112547Abstract: 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: ApplicationFiled: October 26, 2016Publication date: April 26, 2018Inventors: Zachary John Snider, Gregory Thomas Foster, Joseph Anthony Weber, James Fredric Wiedenhoefer
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Patent number: 9932838Abstract: A cooling system according to an embodiment includes: a three-pass serpentine cooling circuit; and an air feed cavity for supplying cooling air to the three-pass serpentine cooling circuit; wherein the three-pass serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum and a first set of near wall cooling channels of a multi-wall blade.Type: GrantFiled: December 21, 2015Date of Patent: April 3, 2018Assignee: General Electric CompanyInventors: Aaron Ezekiel Smith, Gregory Thomas Foster, David Wayne Weber, Joseph Anthony Weber
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Patent number: 9926788Abstract: A cooling system according to an embodiment includes: a serpentine cooling circuit, the serpentine cooling circuit including a first leg extending in a first direction, a second leg extending in a second direction, and a turn fluidly coupling the first leg and the second leg; and an air feed cavity for supplying cooling air to the serpentine cooling circuit; wherein the first leg of the serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the serpentine cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels of the multi-wall blade.Type: GrantFiled: December 21, 2015Date of Patent: March 27, 2018Assignee: General Electric CompanyInventors: Aaron Ezekiel Smith, Gregory Thomas Foster, David Wayne Weber, Joseph Anthony Weber
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Publication number: 20180030837Abstract: 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: ApplicationFiled: July 26, 2016Publication date: February 1, 2018Inventors: Sandip DUTTA, Benjamin Paul LACY, Gary Michael ITZEL, Joseph Anthony WEBER, David Edward SCHICK