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公开(公告)号：US20210404344A1
公开(公告)日：2021-12-30
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
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：US11199098B2
公开(公告)日：2021-12-14
申请号：US16669756
申请日：2019-10-31
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US10605096B2
公开(公告)日：2020-03-31
申请号：US15152690
申请日：2016-05-12
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US10267162B2
公开(公告)日：2019-04-23
申请号：US15239994
申请日：2016-08-18
Applicant: General Electric Company
Abstract: A cooling system for a turbomachine blade including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: a central cavity and a plurality of outer cavities, wherein the central cavity comprises an intermediate passage of the cooling circuit, and wherein a flow of cooling air is fed into the cooling circuit through a first outer cavity of the plurality of outer cavities; and a connection for fluidly connecting a second outer cavity of the plurality of outer cavities to a platform core of the platform, the flow of cooling air passing through the connection into the platform core of the platform.
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公开(公告)号：US10240465B2
公开(公告)日：2019-03-26
申请号：US15334454
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Robert Peter Hanet , Gregory Thomas Foster , Brendon James Leary
Abstract: A trailing edge cooling system for a multi-wall blade, including: a set of outward legs extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a set of return legs extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage; and a connecting system for fluidly coupling the set of outward legs and the set of return legs; wherein the set of outward legs is radially offset from the set of return legs along a radial axis of the multi-wall blade.
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Patent Agency Ranking
公开(公告)号：US20190054567A1
公开(公告)日：2019-02-21
申请号：US15680734
申请日：2017-08-18
Applicant: General Electric Company
IPC: B23K26/342 , B33Y10/00 , B33Y30/00 , B33Y50/02 , B33Y80/00 , B23K26/082 , B23K26/08 , B23K26/144
Abstract: Additive manufactured components including portions having distinct porosities, and systems/methods of forming components including portions having distinct porosities are disclosed. The components may include a first portion having a first porosity. The first portion may include a first exposure pattern of a plurality of scan vectors extending over the first portion. The first exposure pattern may define the first porosity of the first portion. The component may also include a second portion positioned adjacent the first portion. The second portion may include a second porosity greater than the first porosity of the first portion. Additionally, the second portion may include a second exposure pattern of a plurality of scan vectors extending over the second portion. The second exposure pattern may be distinct from the first exposure pattern of the first portion, and may define the second porosity of the second portion.
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公开(公告)号：US10119406B2
公开(公告)日：2018-11-06
申请号：US15152698
申请日：2016-05-12
Applicant: General Electric Company
Inventor： Brendon James Leary , Elisabeth Kraus Black , Gregory Thomas Foster , Michelle Jessica Iduate , Jacob Charles Perry, II
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and forming a radially extending coolant receiving chamber. A rib partitions the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib. Each passage is enclosed at an end of the radially extending chamber by an end member of the radially extending chamber. A turn opening is defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber. A bulbous projection extends along the end of the rib and on opposing radially extending sides of the turn opening to reduce stress in the rib and/or connecting fillets.
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公开(公告)号：US20180112536A1
公开(公告)日：2018-04-26
申请号：US15334517
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Brendon James Leary
CPC classification number: F01D5/186 , F01D5/187 , F01D9/065 , F05D2220/32 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/202
Abstract: A turbine blade airfoil including various internal cavities that are fluidly coupled is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil. The first pressure side cavity may receive a coolant. The airfoil may also include a second pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, and at least one channel positioned between and fluidly coupling the first and second pressure side cavities. The channel may be positioned radially between a top surface and a bottom surface of the first and second pressure side cavities. Additionally, the airfoil may include a trailing edge cooling system positioned adjacent a trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may receive a portion of the coolant from the first pressure side cavity.
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公开(公告)号：US20170175549A1
公开(公告)日：2017-06-22
申请号：US14978224
申请日：2015-12-22
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D9/041 , F05D2220/32 , F05D2240/304 , F05D2260/20 , F05D2260/2212 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; and a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section.
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公开(公告)号：US12065946B2
公开(公告)日：2024-08-20
申请号：US18142577
申请日：2023-05-02
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 airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.
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