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公开(公告)号：US20180320530A1
公开(公告)日：2018-11-08
申请号：US15587974
申请日：2017-05-05
Applicant: General Electric Company
Inventor： Kevin Robert Feldmann , Robert Charles Groves, II , Weston Nolan Dooley , James Michael Hoffman
CPC classification number: F01D5/186 , F01D5/141 , F05D2220/323 , F05D2240/307 , F05D2260/202
Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.
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公开(公告)号：US20180179899A1
公开(公告)日：2018-06-28
申请号：US15387808
申请日：2016-12-22
Applicant: General Electric Company
Inventor： Gregory Terrence Garay , Weston Nolan Dooley
IPC: F01D5/18
CPC classification number: F01D5/20 , F05D2230/10 , F05D2230/237 , F05D2240/307 , F05D2260/202 , Y02T50/676
Abstract: A method and apparatus for brazed engine components include machining an engine component, such as using a casting process, to form an aperture in the component. A brazing material is provided in the aperture to close the aperture and seal an interior of the engine component. A shaped cooling hole is machined in the brazing material to cool the brazing material during engine operation.
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公开(公告)号：US10563518B2
公开(公告)日：2020-02-18
申请号：US15043933
申请日：2016-02-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Douglas Gerard Konitzer , Matthew Lee Krumanaker , Weston Nolan Dooley , James Herbert Deines
Abstract: An apparatus and method for an airfoil for a gas turbine engine includes a trailing edge cooling circuit utilizing a plurality of trailing edge ejection holes. The ejection holes can include a circumferentially radiused inlet, a converging section, a metering section, and a diverging section to improve airfoil cooling as well as castability.
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公开(公告)号：US10443398B2
公开(公告)日：2019-10-15
申请号：US14884100
申请日：2015-10-15
Applicant: General Electric Company
Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.
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公开(公告)号：US20180291742A1
公开(公告)日：2018-10-11
申请号：US15481628
申请日：2017-04-07
Applicant: General Electric Company
Inventor： James Michael Hoffman , Weston Nolan Dooley , Aaron Ezekiel Smith , Steven Robert Brassfield
Abstract: An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.
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Patent Agency Ranking
公开(公告)号：US20180274381A1
公开(公告)日：2018-09-27
申请号：US15467431
申请日：2017-03-23
Applicant: General Electric Company
Inventor： Weston Nolan Dooley , James Michael Hoffman , Gregory Terrence Garay
CPC classification number: F01D11/006 , F01D5/30 , F05D2220/32 , F05D2240/55 , F05D2240/57 , F05D2250/71
Abstract: A turbine engine component includes: a body bounded by an end face; and a seal slot having an opening communicating with the end face, the seal slot including a receptacle defining a boundary configured to receive and position a spline seal, and an open chamber communicating with the seal slot and extending beyond the boundary.
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公开(公告)号：US20180209277A1
公开(公告)日：2018-07-26
申请号：US15412387
申请日：2017-01-23
Applicant: General Electric Company
Inventor： Weston Nolan Dooley , James Michael Hoffman , Steven Robert Brassfield
Abstract: An apparatus relating to engineering the geometry for a ball-chute support feature in an investment casting core. The investment casting core is for an airfoil region having at least one serpentine feature and at least one inlet feature coupled to the at least one serpentine feature by a ball-chute support feature. The investment casting core is leached out to form cooling passages in the airfoil.
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公开(公告)号：US20170107828A1
公开(公告)日：2017-04-20
申请号：US14884100
申请日：2015-10-15
Applicant: General Electric Company
Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.
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公开(公告)号：US20170107824A1
公开(公告)日：2017-04-20
申请号：US14884009
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Steven Robert Brassfield , Robert Frederick Bergholz , Aaron Ezekiel Smith , Weston Nolan Dooley
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D9/041 , F01D25/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/303 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.
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公开(公告)号：US11021969B2
公开(公告)日：2021-06-01
申请号：US16214411
申请日：2018-12-10
Applicant: General Electric Company
Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.
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