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公开(公告)号：US10273810B2
公开(公告)日：2019-04-30
申请号：US15334501
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Brendon James Leary
Abstract: A turbine blade airfoil including cooling circuits is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil, where the first pressure side cavity is configured to receive a coolant. The airfoil may also include at least one distinct pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, a trailing edge positioned between the pressure and a suction side, and a trailing edge cooling system positioned adjacent the trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may be configured to receive a portion of the coolant from the first pressure side cavity.
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公开(公告)号：US20190017389A1
公开(公告)日：2019-01-17
申请号：US15648564
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Thomas Earl Dyson , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
IPC: F01D5/18
Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall (94) enclosing an interior for the airfoil 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 airfoil to cool the tip of the airfoil.
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公开(公告)号：US20180112539A1
公开(公告)日：2018-04-26
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
CPC classification number: F01D5/187 , F01D5/147 , F01D9/041 , F02C3/04 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/35 , F05D2250/185 , F05D2260/202 , F05D2260/205
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：US20180112538A1
公开(公告)日：2018-04-26
申请号：US15334585
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Sandip Dutta , Brendon James Leary
IPC: F01D5/18
Abstract: Various geometries for a trailing edge cooling system for a turbine blade is disclosed. The trailing edge cooling system may include a plurality of cooling circuits extending at least partially along a radial length of a trailing edge of the turbine blade. Each cooling circuit may include an outward leg extending axially toward the trailing edge, and a plurality of turn legs in fluid communication with the outward leg. The plurality of turn legs may be positioned adjacent the trailing edge. Each cooling circuit may also include a return leg positioned adjacent the outward leg and extending axially from the trailing edge. The return leg may include a first portion and a second portion. The first portion may have a first width, and a second may have a second width that is greater than the first width of the first portion.
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公开(公告)号：US09664058B2
公开(公告)日：2017-05-30
申请号：US14587714
申请日：2014-12-31
Applicant: General Electric Company
CPC classification number: F01D11/008 , F01D5/3007 , F04D29/164 , F04D29/321 , F04D29/322 , F04D29/329 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.
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Patent Agency Ranking
公开(公告)号：US11732593B2
公开(公告)日：2023-08-22
申请号：US17519038
申请日：2021-11-04
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/60
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：US11603764B2
公开(公告)日：2023-03-14
申请号：US17270261
申请日：2018-08-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas Earl Dyson , Joseph I Block , Brendon James Leary , Lyndsay Marie Kibler
IPC: F01D5/18
Abstract: An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the article body portion (36); and at least one internal feature (72) disposed at least partially within the article body portion (36) and at least partially within the pedestal (58A, 60A, 84, 86). At least a portion of the internal feature (72) is hollow.
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公开(公告)号：US20220065165A1
公开(公告)日：2022-03-03
申请号：US17008775
申请日：2020-09-01
Applicant: General Electric Company
Inventor： Brendon James Leary , Frederic Woodrow Roberts, JR. , Ibrahim Sezer , Tyler Christopher Henson
IPC: F02C7/05
Abstract: A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.
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公开(公告)号：US20220056805A1
公开(公告)日：2022-02-24
申请号：US17519038
申请日：2021-11-04
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：US10301946B2
公开(公告)日：2019-05-28
申请号：US15334517
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Brendon James Leary
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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