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公开(公告)号：US11732594B2
公开(公告)日：2023-08-22
申请号：US16697242
申请日：2019-11-27
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Thomas Earl Dyson , Brian Brzek
IPC: F01D5/18
CPC classification number: F01D5/189 , F01D5/186 , F05D2240/121 , F05D2240/304 , F05D2250/711 , F05D2260/202 , F05D2260/2212
Abstract: A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.
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公开(公告)号：US11655718B2
公开(公告)日：2023-05-23
申请号：US17316026
申请日：2021-05-10
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D5/141 , F01D5/20 , F01D5/3007 , F05D2220/323 , F05D2240/307 , F05D2260/201 , F05D2260/202 , F05D2260/205
Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
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公开(公告)号：US20220250734A1
公开(公告)日：2022-08-11
申请号：US17173612
申请日：2021-02-11
Applicant: General Electric Company
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.
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公开(公告)号：US20220185446A1
公开(公告)日：2022-06-16
申请号：US17120674
申请日：2020-12-14
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Corey Bourassa , Douglas Carl Hofer , Gregory Alexander Natsui , Brian Magann Rush
IPC: B64C1/38
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.
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公开(公告)号：US20210147087A1
公开(公告)日：2021-05-20
申请号：US16685586
申请日：2019-11-15
Applicant: General Electric Company
Inventor： William Dwight Gerstler , Nicholas William Rathay , Brian Magann Rush , Pazhayannur R. Subramanian
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. The leading edge assembly includes a plurality of structural layers and a plurality compliant layers alternately stacked with each other to facilitate thermal expansion and movement between the plurality of structural layers, while also providing a thermal break between the plurality of structural layers.
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Patent Agency Ranking
公开(公告)号：US10982553B2
公开(公告)日：2021-04-20
申请号：US16207995
申请日：2018-12-03
Applicant: General Electric Company
Abstract: A tip for a turbine component, turbine rotor blade or tip of a blade, is disclosed. The tip includes a tip plate configured to be coupled at a tip end of an airfoil chamber; and a tip rail extending radially from the tip plate, the tip rail disposed near or at a periphery of the tip plate. The trip rail includes a cooling structure constituting at least a portion of the tip rail. The cooling structure is in fluid communication with the airfoil chamber, and includes a plurality of repeating, three dimensional unit cells. Each unit cell defines a flow passage that is in fluid communication with the flow passage of at least one other unit cell. The flow passages of the 3D unit cells create a tortuous cooling passage in at least a portion of the tip rail.
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公开(公告)号：US10933481B2
公开(公告)日：2021-03-02
申请号：US15862927
申请日：2018-01-05
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Jason Ray Gregg , Nicholas William Rathay
Abstract: Methods of forming a cooling passage on a turbine component having a component wall with an internal surface and an external surface, are disclosed. An opening is formed passing through the component wall and fluidly connecting the internal and external surfaces. The opening includes a metering section extending from the internal surface to a metering end, and a diffuser area extending from the metering end to the external surface. A preformed cap element is added to close a portion of the diffuser area to form the cooling passage with a diffusion section extending from the metering end to the external surface. The preformed metal cap element includes a projection extending internally of the external surface and into the diffusion area to define an internally facing section of the diffusion section. The cooling passage extends through the component wall and fluidly connects the internal surface and the external surface.
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公开(公告)号：US10605098B2
公开(公告)日：2020-03-31
申请号：US15648541
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
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公开(公告)号：US20200070961A1
公开(公告)日：2020-03-05
申请号：US16118878
申请日：2018-08-31
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Narendra Digamber Joshi
Abstract: A flow control actuator includes a first side wall, a second side wall opposite and substantially parallel to the first side wall, an upstream wall mechanically coupled to upstream ends of the first and second side walls, and a downstream cap mechanically coupled to downstream ends of the first and second side walls. The first side wall, the second side wall, the upstream wall and the downstream cap collectively define an interior of the flow control actuator. An energy source is disposed in at least one of the first sidewall and the second sidewall. At least one fuel injector is disposed in the upstream wall, the first sidewall and/or the second sidewall for dispersing fuel into the flow control actuator. At least one air inlet is disposed in the upstream wall, the first sidewall and/or the second sidewall for introducing air into the flow control actuator. Fuel from fuel injector and air from the air inlet are ignited in the flow control actuator.
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公开(公告)号：US20200025216A1
公开(公告)日：2020-01-23
申请号：US16039621
申请日：2018-07-19
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Narendra Digamber Joshi
Abstract: A combustion system includes at least one plasma actuator disposed along a substrate at a plasma location, and at least one fuel injector disposed along the substrate at an injection location. The fuel injector disperses fuel toward the plasma location. The plasma from plasma actuator ignites fuel from the fuel injector proximate the plasma location.
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