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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：US10309227B2
公开(公告)日：2019-06-04
申请号：US15334563
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Sandip Dutta
Abstract: A trailing edge cooling system for a turbine blade is disclosed. The system may include a cooling circuit including an outward leg, and a return leg positioned adjacent the outward leg. The outward and return leg each may extend toward and away, respectively, from a trailing edge of the turbine blade. The cooling circuit may also include a plurality of turn legs. The plurality of turn legs may include a turn leg positioned directly adjacent the trailing edge of the turbine blade, and a distinct turn leg positioned axially adjacent the turn leg, and opposite the trailing edge of the turbine blade. The distinct turn leg may be oriented non-parallel to at least one of the outward leg and the return leg.
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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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Patent Agency Ranking
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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公开(公告)号：US10047622B2
公开(公告)日：2018-08-14
申请号：US14337453
申请日：2014-07-22
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
Abstract: The present application provides seal assemblies having improved flexibility for reducing leakages between adjacent misaligned components of turbomachinery. The seal assemblies include a first outer shim formed of a flexible permeable material and a second outer shim formed of a substantially impervious material. At least the second outer shim is configured for sealing engagement with seal slots of the adjacent components. The seal assemblies may also include at least one of an inner shim and a filler layer positioned between the first and second outer shims. The seal assemblies may be sufficiently flexible to account for misalignment between the adjacent components, sufficiently stiff to meet assembly requirements, and sufficiently robust to meet operating requirements associated with turbomachinery. A turbomachine including the seal assembly is provided.
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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：US20180051573A1
公开(公告)日：2018-02-22
申请号：US15239930
申请日：2016-08-18
Applicant: General Electric Company
Inventor： David Wayne Weber , Lana Maria Osusky
CPC classification number: F01D5/187 , F01D25/12 , F05D2250/185 , F05D2260/201 , F05D2260/202
Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the central cavity; a second leading edge cavity located forward of the first leading edge cavity; at least one impingement opening for fluidly coupling the first leading edge cavity to the second leading edge cavity; and at least one channel for fluidly coupling the central cavity to a tip of the multi-wall blade.
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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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