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公开(公告)号：US20170175540A1
公开(公告)日：2017-06-22
申请号：US14977078
申请日：2015-12-21
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/147 , F02C3/04 , F05D2220/32 , F05D2240/307 , F05D2240/35 , F05D2260/202
Abstract: A cooling system according to an embodiment includes: a forked passage cooling circuit, the forked passage cooling circuit including a first leg and a second leg; and an air feed cavity for supplying cooling air to the first leg and the second leg of the forked passage cooling circuit; wherein the first leg of the forked passage cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the forked passage cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels in the multi-wall blade.
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公开(公告)号：US20160186591A1
公开(公告)日：2016-06-30
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.
Abstract translation: 一种具有流路的燃气轮机，其具有转子组件，该转子组件包括：第一转子轮，其支撑具有限定所述流路内边界的第一轴向部分的平台的第一转子叶片; 支撑第二转子叶片的第二转子轮，所述第二转子叶片具有限定所述流动路径的内边界的第二轴向部分的平台; 以及环形填料，其包括外侧表面，所述外侧表面限定出现在所述流动路径的内边界的所述第一轴向部分和所述第二轴向部分之间的所述流动路径的内边界的第三轴向部分的至少一部分。 第一转子轮可以包括用于轴向接合形成在第一转子叶片的径向最内表面上的配合表面的轴向连接器和形成在环形填料的径向最内表面上的配合表面。
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公开(公告)号：US11525397B2
公开(公告)日：2022-12-13
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：US11225707B2
公开(公告)日：2022-01-18
申请号：US16539803
申请日：2019-08-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Lyndsay Marie Kibler , Brendon James Leary , David Vincent Bucci
Abstract: A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.
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公开(公告)号：US11035237B2
公开(公告)日：2021-06-15
申请号：US16793138
申请日：2020-02-18
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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Patent Agency Ranking
公开(公告)号：US20210115944A1
公开(公告)日：2021-04-22
申请号：US16654496
申请日：2019-10-16
Applicant: General Electric Company
Inventor： Sylvain Pierre , Brendon James Leary , Jason Adam Neville
Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US20200300097A1
公开(公告)日：2020-09-24
申请号：US16793138
申请日：2020-02-18
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：US10753207B2
公开(公告)日：2020-08-25
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
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：US10646959B2
公开(公告)日：2020-05-12
申请号：US15680741
申请日：2017-08-18
Applicant: General Electric Company
IPC: B33Y80/00 , B33Y10/00 , B23K26/342 , B24C1/10 , B33Y99/00
Abstract: Additive manufactured components including sacrificial caps, and methods of forming components including sacrificial caps are disclosed. The additive manufactured components may include a body portion including a first surface, and a feature formed in the body portion. The feature may include an aperture formed through the first surface of the body portion. Additionally, the components may include a sacrificial cap formed integral with at least a portion of the first surface of the body portion. The sacrificial cap may include a conduit in fluid communication with the feature. The sacrificial cap including the conduit may be removed from the body portion to expose the first surface and the aperture of the feature, respectively, after performing one or more post-build processes, such as shot peening, on the component and the sacrificial cap.
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公开(公告)号：US10450875B2
公开(公告)日：2019-10-22
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. 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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