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公开(公告)号：US20210017907A1
公开(公告)日：2021-01-21
申请号：US17060162
申请日：2020-10-01
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：US20180355755A1
公开(公告)日：2018-12-13
申请号：US15441586
申请日：2017-02-24
Applicant: General Electric Company
Inventor： Robert Charles Groves, II , David Scott Stapleton
CPC classification number: F01D25/12 , F01D11/005 , F01D11/08 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2250/12 , F05D2250/72 , F05D2260/201 , F05D2270/112
Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.
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公开(公告)号：US20180223681A1
公开(公告)日：2018-08-09
申请号：US15428722
申请日：2017-02-09
Applicant: General Electric Company
Inventor： Kirk D. Gallier , Robert Charles Groves, II
CPC classification number: F01D25/12 , F01D11/005 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2300/6033 , Y02T50/676
Abstract: An apparatus for a shroud assembly for a turbine engine and a method of manufacturing such can include the shroud assembly having one or more shroud segments having an inner face in a circumferential organization around a rotating blade assembly. A near wall cooling passage can be provided in the shroud assembly to cool the inner face of the shroud. The near wall cooling passage can exhaust to a purge cavity, a split line, or at the inner face.
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公开(公告)号：US20240310224A1
公开(公告)日：2024-09-19
申请号：US18676779
申请日：2024-05-29
Applicant: General Electric Company
Inventor： Kirk D. Gallier , Robert Charles Groves, II
IPC: G01L1/20 , G01L1/22 , G01L5/1627 , G02F1/1333 , G02F1/1345 , G02F1/1362
CPC classification number: G01L1/205 , G01L1/2206 , G01L5/1627 , G02F1/13452 , G02F1/133302 , G02F1/13454 , G02F1/136254
Abstract: An apparatus for a shroud assembly for a turbine engine and a method of manufacturing such can include the shroud assembly having one or more shroud segments having an inner face in a circumferential organization around a rotating blade assembly. A near wall cooling passage can be provided in the shroud assembly to cool the inner face of the shroud. The near wall cooling passage can exhaust to a purge cavity, a split line, or at the inner face.
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公开(公告)号：US10472972B2
公开(公告)日：2019-11-12
申请号：US14955261
申请日：2015-12-01
Applicant: General Electric Company
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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Patent Agency Ranking
公开(公告)号：US20180355741A1
公开(公告)日：2018-12-13
申请号：US15441495
申请日：2017-02-24
Applicant: General Electric Company
Inventor： Robert Charles Groves, II , David Scott Stapleton
CPC classification number: F01D11/005 , F01D11/08 , F01D25/12 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2240/57 , F05D2250/12 , F05D2250/72 , F05D2260/201
Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.
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公开(公告)号：US11591966B2
公开(公告)日：2023-02-28
申请号：US17060162
申请日：2020-10-01
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：US10655495B2
公开(公告)日：2020-05-19
申请号：US15441537
申请日：2017-02-24
Applicant: General Electric Company
Inventor： Robert Charles Groves, II , David Scott Stapleton
Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.
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公开(公告)号：US10519779B2
公开(公告)日：2019-12-31
申请号：US15071443
申请日：2016-03-16
Applicant: General Electric Company
Inventor： Robert Charles Groves, II , Kirk Douglas Gallier , Ronald Scott Bunker
Abstract: An airfoil having a radial direction extending away from an engine axis is provided. The airfoil includes an airfoil wall having an airfoil outer surface and an airfoil inner surface, with the airfoil extending radially from a first end to a second end. The airfoil defines a cooling channel interior to the inner surface with a thickness being defined between the airfoil outer surface and the airfoil inner surface. The thickness varies in the radial direction from the first end to the second end along at least one radial cross-section of the airfoil. A turbine nozzle of a turbine engine is also provided, which may include an outer band, an inner band, and the airfoil.
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公开(公告)号：US20180355753A1
公开(公告)日：2018-12-13
申请号：US15441537
申请日：2017-02-24
Applicant: General Electric Company
Inventor： Robert Charles Groves, II , David Scott Stapleton
CPC classification number: F01D25/12 , F01D5/14 , F01D11/005 , F01D11/08 , F01D11/14 , F01D25/24 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2250/12 , F05D2250/72 , F05D2260/201 , F05D2270/112
Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.
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