Patents by Inventor Russell Pierson DeForest
Russell Pierson DeForest 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: 11773739Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.Type: GrantFiled: June 25, 2021Date of Patent: October 3, 2023Assignee: General Electric CompanyInventors: Neelesh Nandkumar Sarawate, Jonathan Dwight Berry, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Klara Sezer, Deepak Trivedi
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Patent number: 11236628Abstract: A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile.Type: GrantFiled: January 22, 2021Date of Patent: February 1, 2022Assignee: General Electric CompanyInventors: Neil Devin Ristau, Russell Pierson DeForest, Jalindar Appa Walunj
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Patent number: 11231175Abstract: An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.Type: GrantFiled: June 19, 2018Date of Patent: January 25, 2022Assignee: General Electric CompanyInventors: Jonathan Dwight Berry, Michael John Hughes, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Sezer, Neelesh Nandkumar Sarawate, Deepak Trivedi
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Publication number: 20210324754Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.Type: ApplicationFiled: June 25, 2021Publication date: October 21, 2021Inventors: Neelesh Nandkumar Sarawate, Jonathan Dwight Berry, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Klara Sezer, Deepak Trivedi
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Patent number: 11047248Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.Type: GrantFiled: June 19, 2018Date of Patent: June 29, 2021Assignee: General Electric CompanyInventors: Neelesh Nandkumar Sarawate, Jonathan Dwight Berry, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Sezer, Deepak Trivedi
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Patent number: 10900362Abstract: An insert system for an airfoil plenum includes a first insert and a second insert that include a plurality of impingement openings defined therein. The first insert includes a forward-facing inlet opening. The second insert includes a neck portion having a radial-facing inlet opening, an aft opening, and a cavity in flow communication between the radial-facing inlet opening and the aft opening. The second insert is sized for insertion into the plenum radially through a plenum inlet such that the neck portion is positioned in the plenum inlet. The first insert is sized for insertion into the second insert radially through the radial-facing inlet opening. When the neck portion is positioned in the plenum inlet, the first insert is moveable aftward through the aft opening into an installed position such that the forward-facing inlet opening opens into the cavity.Type: GrantFiled: January 14, 2019Date of Patent: January 26, 2021Assignee: General Electric CompanyInventors: Jonathan Dwight Berry, Matthew Troy Hafner, Russell Pierson DeForest
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Publication number: 20200224540Abstract: An insert system for an airfoil plenum includes a first insert and a second insert that include a plurality of impingement openings defined therein. The first insert includes a forward-facing inlet opening. The second insert includes a neck portion having a radial-facing inlet opening, an aft opening, and a cavity in flow communication between the radial-facing inlet opening and the aft opening. The second insert is sized for insertion into the plenum radially through a plenum inlet such that the neck portion is positioned in the plenum inlet. The first insert is sized for insertion into the second insert radially through the radial-facing inlet opening. When the neck portion is positioned in the plenum inlet, the first insert is moveable aftward through the aft opening into an installed position such that the forward-facing inlet opening opens into the cavity.Type: ApplicationFiled: January 14, 2019Publication date: July 16, 2020Inventors: Jonathan Dwight Berry, Matthew Troy Hafner, Russell Pierson DeForest
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Publication number: 20190383488Abstract: An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.Type: ApplicationFiled: June 19, 2018Publication date: December 19, 2019Applicant: General Electric CompanyInventors: Jonathan Dwight Berry, Michael John Hughes, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Sezer, Neelesh Nandkumar Sarawate, Deepak Trivedi
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Publication number: 20190383156Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.Type: ApplicationFiled: June 19, 2018Publication date: December 19, 2019Applicant: General Electric CompanyInventors: Neelesh Nandkumar Sarawate, Jonathan Dwight Berry, Russell Pierson DeForest, Kevin Weston McMahan, Victor John Morgan, Ibrahim Sezer, Deepak Trivedi
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Patent number: 10156149Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the airfoil having a fillet at the trailing edge proximate the at least one endwall.Type: GrantFiled: February 9, 2016Date of Patent: December 18, 2018Assignee: General Electric CompanyInventors: Neil Ristau, Russell Pierson DeForest, William Ladd Rutherford
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Publication number: 20170226879Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the airfoil having a fillet at the trailing edge proximate the at least one endwall.Type: ApplicationFiled: February 9, 2016Publication date: August 10, 2017Inventors: Neil Ristau, Russell Pierson DeForest, William Ladd Rutherford
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Patent number: 9140455Abstract: A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture.Type: GrantFiled: January 4, 2012Date of Patent: September 22, 2015Assignee: General Electric CompanyInventors: Lucas John Stoia, Russell Pierson DeForest, Patrick Benedict Melton
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Publication number: 20130167542Abstract: A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture.Type: ApplicationFiled: January 4, 2012Publication date: July 4, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Lucas John Stoia, Russell Pierson DeForest, Patrick Benedict Melton