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公开(公告)号：US20200182059A1
公开(公告)日：2020-06-11
申请号：US16210314
申请日：2018-12-05
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Kirk Douglas Gallier , Brandon Wayne Miller , Craig Alan Gonyou , Kevin Robert Feldmann , Justin Paul Smith
Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.
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公开(公告)号：US20170218784A1
公开(公告)日：2017-08-03
申请号：US15014057
申请日：2016-02-03
Applicant: General Electric Company
Inventor： Kevin Robert Feldmann , Aaron Ezekiel Smith
CPC classification number: F01D11/005 , F01D9/041 , F05D2220/32 , F05D2240/57 , F05D2250/74 , F05D2250/75 , F16J15/02 , F16J15/46 , F16J15/48 , Y02T50/673
Abstract: Embodiments of the invention relate to a turbine assembly including a shroud assembly and a nozzle assembly axially adjacent to each other which both include confronting radial sides and confronting axial ends. A spline connector having a circumferential portion and an axial portion such that the circumferential portion of the spline connector extends across the axial ends and the axial portion of the spline connector extends across the confronting radial sides.
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公开(公告)号：US20170152749A1
公开(公告)日：2017-06-01
申请号：US14955261
申请日：2015-12-01
Applicant: General Electric Company
CPC classification number: F01D5/186 , C23C28/321 , C23C28/345 , F01D5/288 , F01D9/065 , F05D2230/30 , F05D2230/90 , F05D2260/202 , F05D2300/15 , F05D2300/211 , F05D2300/5024 , F05D2300/6033 , F23R3/007 , F23R3/06 , F23R2900/03042 , Y02T50/672 , Y02T50/676 , Y02T50/6765
Abstract: Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate generally defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.
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公开(公告)号：US20250027417A1
公开(公告)日：2025-01-23
申请号：US18440316
申请日：2024-02-13
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.
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公开(公告)号：US20240254885A1
公开(公告)日：2024-08-01
申请号：US18599470
申请日：2024-03-08
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
CPC classification number: F01D5/186 , F01D25/12 , F05D2220/32 , F05D2240/30 , F05D2260/202
Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.
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Patent Agency Ranking
公开(公告)号：US11187094B2
公开(公告)日：2021-11-30
申请号：US16550363
申请日：2019-08-26
Applicant: General Electric Company
Inventor： Kevin Robert Feldmann , Robert Proctor , David Scott Stapleton , Robert Charles Groves, II
Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.
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公开(公告)号：US10563867B2
公开(公告)日：2020-02-18
申请号：US14870829
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Kevin Robert Feldmann , Douglas Ray Smith , Kirk D. Gallier , Daniel Scott Martyn , Rachel Anne Vukoja
Abstract: An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component also includes a flow conditioning structure provided upstream of the outlet on the hot surface. The flow conditioning structure can include a ridge extending from the hot surface.
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公开(公告)号：US10563519B2
公开(公告)日：2020-02-18
申请号：US15898716
申请日：2018-02-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann , Steven Robert Brassfield
Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.
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公开(公告)号：US10450874B2
公开(公告)日：2019-10-22
申请号：US15043513
申请日：2016-02-13
Applicant: General Electric Company
Abstract: A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.
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公开(公告)号：US10161257B2
公开(公告)日：2018-12-25
申请号：US14887537
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Benjamin Scott Huizenga , Kevin Robert Feldmann , Robert Alan Frederick , Robert Charles Groves, II , Kirk Douglas Gallier , Timothy Francis Andrews , Darrell Senile
Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectively. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.
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