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公开(公告)号：US20210324744A1
公开(公告)日：2021-10-21
申请号：US16851371
申请日：2020-04-17
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek
Abstract: A rotor blade for use in a turbine of a combustion turbine engine comprises an airfoil, which includes a concave pressure and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between base and outboard tip end. The rotor blade further including at least one mid-span shroud engages a corresponding mid-span shroud on at least one neighboring rotor blade. The airfoil includes an inboard region between the at least one mid-span shroud and base of the blade-and an outboard region between at least one mid-span shroud and outward tip. The outboard region includes at least two cavities extending from the outboard tip end inboard toward the at least one mid-span shroud; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.
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公开(公告)号：US11566525B1
公开(公告)日：2023-01-31
申请号：US17890479
申请日：2022-08-18
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Kristen Barbara Coletti , Jan Emeric Agudo
IPC: F01D5/14
Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with 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 to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.
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公开(公告)号：US20210324746A1
公开(公告)日：2021-10-21
申请号：US16850661
申请日：2020-04-16
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek
Abstract: The present embodiments set forth a blade including an airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the tip cap. The airfoil further includes a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall and around the leading edge and trailing edge. The tip cap includes a squealer tip configuration including a suction side tip cap portion and a pressure side tip cap portion. The suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor providing for cooling fluid flow out of the tip cap.
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公开(公告)号：US11236628B1
公开(公告)日：2022-02-01
申请号：US17155427
申请日：2021-01-22
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Russell Pierson DeForest , Jalindar Appa Walunj
Abstract: 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.
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公开(公告)号：US11168569B1
公开(公告)日：2021-11-09
申请号：US16851371
申请日：2020-04-17
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek
Abstract: A rotor blade for use in a turbine of a combustion turbine engine comprises an airfoil, which includes a concave pressure and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between base and outboard tip end. The rotor blade further including at least one mid-span shroud engages a corresponding mid-span shroud on at least one neighboring rotor blade. The airfoil includes an inboard region between the at least one mid-span shroud and base of the blade—and an outboard region between at least one mid-span shroud and outward tip. The outboard region includes at least two cavities extending from the outboard tip end inboard toward the at least one mid-span shroud; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.
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Patent Agency Ranking
公开(公告)号：US20210246792A1
公开(公告)日：2021-08-12
申请号：US16784811
申请日：2020-02-07
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek , Jan Emeric Agudo
Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: 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 to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.
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公开(公告)号：US11339670B2
公开(公告)日：2022-05-24
申请号：US17069434
申请日：2020-10-13
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek
Abstract: A blade airfoil including a platform, concave pressure sidewall and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and outboard tip. The blade further includes at least one part-span shroud positioned on the airfoil defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying values by a length of the at least one part-span shroud. X and Y values are connected by continuing arcs to define part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, profile sections at Z distances being joined with one another to form the nominal profile.
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公开(公告)号：US20220112811A1
公开(公告)日：2022-04-14
申请号：US17069434
申请日：2020-10-13
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek
IPC: F01D5/14
Abstract: A blade airfoil including a platform, concave pressure sidewall and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and outboard tip. The blade further includes at least one part-span shroud positioned on the airfoil defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying values by a length of the at least one part-span shroud. X and Y values are connected by continuing arcs to define part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, profile sections at Z distances being joined with one another to form the nominal profile.
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公开(公告)号：US11299991B2
公开(公告)日：2022-04-12
申请号：US16850661
申请日：2020-04-16
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek
Abstract: The present embodiments set forth a blade including an airfoil including an outer tip having a floor, a leading edge and a trailing edge, a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the floor and the tip cap. The airfoil further includes a tip cap extending from the floor of the outer tip and coextensive with the pressure sidewall and suction sidewall and around the leading edge and trailing edge. The tip cap includes a squealer tip configuration including a suction side tip cap portion and a pressure side tip cap portion. The suction side tip cap portion and pressure side tip cap portion extend unequal distances above the floor providing for cooling fluid flow out of the tip cap.
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公开(公告)号：US11156096B2
公开(公告)日：2021-10-26
申请号：US16784811
申请日：2020-02-07
Applicant: General Electric Company
Inventor： Neil Devin Ristau , Michael Anthony Wondrasek , Jan Emeric Agudo
Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: 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 to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.
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