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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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公开(公告)号：US20220341339A1
公开(公告)日：2022-10-27
申请号：US17685523
申请日：2022-03-03
Applicant: General Electric Company
Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.
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公开(公告)号：US11359494B2
公开(公告)日：2022-06-14
申请号：US16532787
申请日：2019-08-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Kirk Douglas Gallier , Daniel Lee Durstock , Zachary Daniel Webster , Gregory Terrence Garay
IPC: F01D5/18
Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.
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公开(公告)号：US20210285332A1
公开(公告)日：2021-09-16
申请号：US16817742
申请日：2020-03-13
Applicant: General Electric Company
Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.
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Patent Agency Ranking
公开(公告)号：US11085315B2
公开(公告)日：2021-08-10
申请号：US16505888
申请日：2019-07-09
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier , David Alan Frey
Abstract: An apparatus and method of sealing for an engine component between two surfaces arranged in spaced relationship to define a gap. A groove located is located in one of the two surface for receiving a seal having a body with a multi-faceted cross-sectional shape defining multiple seal facets. At least one of the multiple seal facets contacts one or both of the two surfaces.
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公开(公告)号：US10794289B2
公开(公告)日：2020-10-06
申请号：US15231846
申请日：2016-08-09
Applicant: General Electric Company
Abstract: Features and methods for modulating a flow of cooling fluid to gas turbine engine components are provided. In one embodiment, an airfoil is provided having a flow modulation insert for modulating a flow of cooling fluid received in a cavity of a body of the airfoil. In another embodiment, a shroud is provided comprising a cooling channel for a flow of cooling fluid and an insert that varies in position to modulate the flow of cooling fluid through the cooling channel. In yet another embodiment, a method for operating a gas turbine engine having a cooling circuit for cooling one or more components of the gas turbine engine comprises increasing power provided to the engine and decreasing power provided to the engine to modulate a position of a flow modulation insert located in the cooling circuit and thereby modulate the flow of cooling fluid through the cooling circuit.
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公开(公告)号：US10458251B2
公开(公告)日：2019-10-29
申请号：US15130013
申请日：2016-04-15
Applicant: General Electric Company
Inventor： Kirk Douglas Gallier
Abstract: An airfoil for a gas turbine engine is provided that includes a first portion formed from a first plurality of plies of a ceramic matrix composite material and defining an inner surface of the airfoil, as well as a second portion formed from a second plurality of plies of a ceramic matrix composite material and defining an outer surface of the airfoil. The first portion and the second portion define a non-line of sight cooling aperture extending from the inner surface to the outer surface of the airfoil. In one embodiment, a surface angle that is less than 45° is defined between a second aperture and the outer surface. A method for forming an airfoil for a gas turbine engine also is provided.
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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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30.发明申请公开(公告)号：US20180328189A1
公开(公告)日：2018-11-15
申请号：US15592516
申请日：2017-05-11
Applicant: General Electric Company
Inventor： David Alan Frey , Kirk Douglas Gallier , Herbert Chidsey Roberts
CPC classification number: F01D5/147 , B23P15/02 , F01D5/14 , F01D5/18 , F01D5/28 , F01D5/284 , F01D9/02 , F01D25/12 , F04D29/32 , F04D29/38 , F04D29/54 , F04D29/58 , F05D2260/204 , F05D2300/6033 , F05D2300/608
Abstract: CMC components having microchannels and methods for forming microchannels in CMC components are provided. For example, a method for forming microchannels in a CMC component comprises laying up a plurality of body plies for forming a body of the CMC component; laying up a microchannel ply on the plurality of body plies that has at least one void therein for forming at least one microchannel; laying up a cover ply on the microchannel ply to define an outer layer of the CMC component; and processing the laid up body plies, microchannel ply, and cover ply to form the CMC component. In another embodiment, the method comprises applying an additive matrix to the body plies to define at least one microchannel. In still other embodiments, the method comprises machining at least one microchannel in the plurality of body plies.
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