Patents by Inventor Fred Thomas Willett, Jr.
Fred Thomas Willett, Jr. 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: 11326462Abstract: A gas turbine spacer disk includes a disk portion, a rim portion, a first fillet, and a second fillet. The disk portion is disposed about a rotational axis. The rim portion is disposed about the disk portion. An outer face of the rim portion defines a plurality grooves extending circumferentially about the rotational axis. The first fillet transitions from the rim portion to a first side of the disk portion. The second fillet transitions from the rim portion to a second side of the disk portion. The plurality of grooves includes a pair of first grooves having a first diameter and a pair of second grooves having a second diameter that is less than the first diameter. A first one of the first grooves overlaps in an axial direction with the first fillet. A second one of the first grooves overlaps in the axial direction with the second fillet.Type: GrantFiled: February 21, 2020Date of Patent: May 10, 2022Assignee: Mechanical Dynamics & Analysis LLCInventor: Fred Thomas Willett, Jr.
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Publication number: 20210262348Abstract: A gas turbine spacer disk includes a disk portion, a rim portion, a first fillet, and a second fillet. The disk portion is disposed about a rotational axis. The rim portion is disposed about the disk portion. An outer face of the rim portion defines a plurality grooves extending circumferentially about the rotational axis. The first fillet transitions from the rim portion to a first side of the disk portion. The second fillet transitions from the rim portion to a second side of the disk portion. The plurality of grooves includes a pair of first grooves having a first diameter and a pair of second grooves having a second diameter that is less than the first diameter. A first one of the first grooves overlaps in an axial direction with the first fillet. A second one of the first grooves overlaps in the axial direction with the second fillet.Type: ApplicationFiled: February 21, 2020Publication date: August 26, 2021Applicant: Mechanical Dynamics & Analysis LLCInventor: Fred Thomas WILLETT, JR.
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Patent number: 10344599Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes an airfoil, a tip shroud having a side surface and a radially outer surface, and a transition portion coupling the tip shroud to the airfoil. The airfoil, the transition portion, and the tip shroud collectively define a primary cooling passage therein. The primary cooling passage includes a primary cooling passage outlet defined by the side surface of the tip shroud.Type: GrantFiled: May 24, 2016Date of Patent: July 9, 2019Assignee: General Electric CompanyInventor: Fred Thomas Willett, Jr.
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Publication number: 20190093483Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.Type: ApplicationFiled: November 13, 2018Publication date: March 28, 2019Applicant: General Electric CompanyInventors: Ariel Caesar Prepena Jacala, Fred Thomas Willett, JR.
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Patent number: 10215033Abstract: A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady state operation section that facilitates a tighter clearance.Type: GrantFiled: April 18, 2012Date of Patent: February 26, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Fred Thomas Willett, Jr., Michael Earl Montgomery, Peter John Eisenzopf, Richard James Miller
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Patent number: 10156142Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.Type: GrantFiled: November 24, 2015Date of Patent: December 18, 2018Assignee: General ELectric CompanyInventors: Ariel Caesar Prepena Jacala, Fred Thomas Willett, Jr.
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Patent number: 10099276Abstract: A method of forming a component having an internal passage defined therein includes positioning a jacketed core with respect to a mold. The jacketed core includes a hollow structure that includes an interior portion shaped to define at least one interior passage feature of the internal passage. The jacketed core also includes an inner core disposed within the hollow structure and complementarily shaped by the interior portion of the hollow structure. The method also includes introducing a component material in a molten state into a cavity of the mold to form the component, such that the inner core defines the internal passage including the at least one interior passage feature defined therein.Type: GrantFiled: December 17, 2015Date of Patent: October 16, 2018Assignee: General Electric CompanyInventors: Timothy Michael Moricca, Stephen Francis Rutkowski, Joseph Leonard Moroso, Fred Thomas Willett, Jr.
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Patent number: 10066485Abstract: A turbomachine blade may include an airfoil and a shank coupled to the airfoil. The shank may include a cover plate having a first circumferential face and a second, opposing circumferential face. A radial cooling groove is positioned in the first circumferential face and is configured to allow a cooling fluid to pass from a first radial position to a second, different radial position relative to the platform. The radial cooling groove provides cover plate and shank cooling. In addition, the radial cooling groove may deliver fluid for purging gaps between blade platforms and cover plates, which prevents the ingestion of hot gas from the turbine flowpath.Type: GrantFiled: December 4, 2015Date of Patent: September 4, 2018Assignee: General Electric CompanyInventors: Fred Thomas Willett, Jr., Eric David Roush
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Publication number: 20170342843Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes an airfoil, a tip shroud having a side surface and a radially outer surface, and a transition portion coupling the tip shroud to the airfoil. The airfoil, the transition portion, and the tip shroud collectively define a primary cooling passage therein. The primary cooling passage includes a primary cooling passage outlet defined by the side surface of the tip shroud.Type: ApplicationFiled: May 24, 2016Publication date: November 30, 2017Inventor: Fred Thomas Willett, JR.
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Publication number: 20170173669Abstract: A method of forming a component having an internal passage defined therein includes positioning a jacketed core with respect to a mold. The jacketed core includes a hollow structure that includes an interior portion shaped to define at least one interior passage feature of the internal passage. The jacketed core also includes an inner core disposed within the hollow structure and complementarily shaped by the interior portion of the hollow structure. The method also includes introducing a component material in a molten state into a cavity of the mold to form the component, such that the inner core defines the internal passage including the at least one interior passage feature defined therein.Type: ApplicationFiled: December 17, 2015Publication date: June 22, 2017Inventors: Timothy Michael Moricca, Stephen Francis Rutkowski, Joseph Leonard Moroso, Fred Thomas Willett, JR.
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Publication number: 20170175543Abstract: A turbine blade cooling system according to an embodiment includes: a first arcuate turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second arcuate turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum of the turbine blade, wherein the first and second arcuate turns reduce impingement of the first flow of gas and the second flow of gas in the central plenum of the turbine blade.Type: ApplicationFiled: December 21, 2015Publication date: June 22, 2017Inventors: David Wayne Weber, Fred Thomas Willett, JR.
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Publication number: 20170159440Abstract: A turbomachine blade may include an airfoil and a shank coupled to the airfoil. The shank may include a cover plate having a first circumferential face and a second, opposing circumferential face. A radial cooling groove is positioned in the first circumferential face and is configured to allow a cooling fluid to pass from a first radial position to a second, different radial position relative to the platform. The radial cooling groove provides cover plate and shank cooling. In addition, the radial cooling groove may deliver fluid for purging gaps between blade platforms and cover plates, which prevents the ingestion of hot gas from the turbine flowpath.Type: ApplicationFiled: December 4, 2015Publication date: June 8, 2017Inventors: Fred Thomas Willett, JR., Eric David Roush
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Publication number: 20170145830Abstract: A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.Type: ApplicationFiled: November 24, 2015Publication date: May 25, 2017Applicant: General Electric CompanyInventors: Ariel Caesar Prepena Jacala, Fred Thomas Willett, JR.
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Publication number: 20170067344Abstract: Provided are a method of forming a rotating component. The method for forming a rotating component includes providing a rotor having an outer surface. A circumferential surface feature is formed on the outer surface of the rotor. The forming includes applying metallic material to the outer surface of the rotor to build up the circumferential surface feature on outer surface of the rotor to define at least one cooling passageway. A rotating component having a circumferential surface feature, a turbine system and an apparatus for forming the rotating component are also disclosed.Type: ApplicationFiled: September 3, 2015Publication date: March 9, 2017Inventors: Fred Thomas WILLETT, JR., Xiaoqing ZHENG
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Patent number: 9587511Abstract: A system and method for measuring and adjusting rotor to stator clearances is disclosed, as well as a turbomachine embodying the system and method. In an embodiment, a turbomachine is assembled, including a stator having an upper and a lower stator shell, and a rotor disposed within the stator. A cold clearance between the rotor and the stator is determined at each of a plurality of clearance measurement points using an in situ clearance sensor system. Each of the clearance measurement points is axially spaced from each other clearance measurement point. The cold clearance between the rotor and the stator is adjusted based on the determined cold clearances, by displacing one of the upper stator shell or the lower stator shell relative to a foundation, thereby changing a shape of the upper stator shell or the lower stator shell to accommodate a position of the rotor within the stator.Type: GrantFiled: December 13, 2013Date of Patent: March 7, 2017Assignee: General Electric CompanyInventors: Fred Thomas Willett, Jr., Kenneth Michael Koza
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Patent number: 9441501Abstract: A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.Type: GrantFiled: October 4, 2013Date of Patent: September 13, 2016Assignee: General Electric CompanyInventors: Henry Grady Ballard, Jr., Fred Thomas Willett, Jr.
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Patent number: 9435217Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.Type: GrantFiled: October 6, 2015Date of Patent: September 6, 2016Assignee: General Electric CompanyInventors: Xiaoqing Zheng, Daniel Mark Brown, Jason Winfred Jewett, Fred Thomas Willett, Jr.
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Patent number: 9394801Abstract: A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions.Type: GrantFiled: October 7, 2013Date of Patent: July 19, 2016Assignee: General Electric CompanyInventor: Fred Thomas Willett, Jr.
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Publication number: 20160186577Abstract: A blade in a turbine of a gas turbine engine that includes: an outer surface bending along an edge at an angle greater than about 120° so to define a first outer surface to a first side of the edge and a second outer surface to a second side of the edge; an internal flow passage; and a forked cooling channel configured so to fluidly connect the internal flow passage to a first film cooling port and a second film cooling port formed to each side of the edge.Type: ApplicationFiled: December 30, 2014Publication date: June 30, 2016Inventor: Fred Thomas Willett, JR.
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Publication number: 20160024954Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.Type: ApplicationFiled: October 6, 2015Publication date: January 28, 2016Inventors: Xiaoqing Zheng, Daniel Mark Brown, Jason Winfred Jewett, Fred Thomas Willett, JR.