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公开(公告)号：US09169733B2
公开(公告)日：2015-10-27
申请号：US13847839
申请日：2013-03-20
Applicant: General Electric Company
Inventor： Onika Misasha Kerber , Gary Michael Itzel , James William Vehr , Evan Andrew Sewall
CPC classification number: F01D5/188 , F01D5/189 , F05D2240/303 , F05D2260/201
Abstract: A turbine airfoil assembly has an airfoil with an inner wall, an outer wall, a leading edge and a trailing edge. The airfoil has one or more chambers extending in a substantially chordwise direction of the airfoil. An insert has a plurality of impingement holes, and the insert is configured to be inserted within one of the chambers. The insert is configured to cool the airfoil via the plurality of impingement holes. A chambering element is attached only to the insert, the chambering element is configured to provide an increased cooling gas pressure inside a boundary area defined by the chambering element relative to an area outside the boundary area. A gap exists between the inner wall of the airfoil and the chambering element, and the gap allows cooling gas to exit the boundary area and enter the area outside the boundary area.
Abstract translation: 涡轮机翼型组件具有具有内壁，外壁，前缘和后缘的翼型件。 翼型件具有在翼型件的大致弦向方向上延伸的一个或多个腔室。 插入件具有多个冲击孔，并且插入件构造成插入在一个室内。 该插入件构造成经由多个冲击孔来冷却翼型件。 腔室元件仅附接到插入件，腔室元件构造成在由腔室元件限定的边界区域内相对于边界区域外的区域提供增加的冷却气体压力。 在翼型件的内壁和加料元件之间存在间隙，并且间隙允许冷却气体离开边界区域并进入边界区域外的区域。
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公开(公告)号：US20140341720A1
公开(公告)日：2014-11-20
申请号：US13893729
申请日：2013-05-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Dipankar Pal , Robert Walter Coign , Gary Michael Itzel , Kevin Thomas McGovern , Christopher Donald Porter
IPC: F01D25/00
CPC classification number: F01D11/005 , F01D11/006 , F05D2240/57
Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.
Abstract translation: 公开了被配置为密封涡轮机的固定部件之间的接口/间隙并且在涡轮机操作期间操纵涡轮机部分周围的冷却剂流的系统和装置。 在一个实施例中，密封元件包括：成形为朝向涡轮的加压腔定向的第一表面; 第二表面，其定向成基本上与第一表面相对并且成形为密封地接合静态部件的接触表面; 以及设置在所述第二表面中的第一组角特征，所述第一组角特征将所述加压腔和所述涡轮的流路流体连接。
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公开(公告)号：US20140157792A1
公开(公告)日：2014-06-12
申请号：US13709306
申请日：2012-12-10
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D5/187 , F01D5/288 , F05D2260/204 , F05D2260/205
Abstract: A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum.
Abstract translation: 用于从涡轮机去除热量的系统包括涡轮机中的部件，其中具有供应气室和回流室。 限定部件形状的基板具有内表面和外表面。 施加到基板的外表面的涂层具有面向基板的外表面的内表面和与内表面相对的外表面。 第一流体通道位于基底的外表面和涂层的外表面之间。 第一流体路径来自供应气室，通过基底，并进入第一流体通道，第二流体路径来自第一流体通道，穿过基底，并进入回流通气室。
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44.发明申请SEALING ARRANGEMENT FOR A TURBINE SYSTEM AND METHOD OF SEALING BETWEEN TWO TURBINE COMPONENTS 有权用于涡轮机系统的密封装置和两个涡轮机部件之间的密封方法公开(公告)号：US20140112753A1
公开(公告)日：2014-04-24
申请号：US13654822
申请日：2012-10-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xiuzhang James Zhang , Gary Michael Itzel , Ibrahim Sezer
IPC: F03B11/00
CPC classification number: F01D11/006 , F01D11/122
Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.
Abstract translation: 涡轮机系统的密封装置包括具有外部尖端的桶，以及从外部末端径向向外延伸的至少一个铲斗脊，所述至少一个铲斗脊包含可磨损材料。 还包括从桶的外端径向向外设置的固定护罩。 还包括至少一个护罩脊，其从固定护罩朝向桶的外部末端径向向内延伸，所述至少一个护罩脊包括可磨损材料。
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公开(公告)号：US20140102684A1
公开(公告)日：2014-04-17
申请号：US13651601
申请日：2012-10-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ibrahim Sezer , Gary Michael Itzel
Abstract: A component for use in a hot gas path of a turbomachine, and a method of constructing the same are disclosed. In an embodiment, the component includes an exterior wall substrate, wherein the exterior wall substrate includes an interior face and an exterior face, and a plurality of plateaus disposed on the exterior face. A plurality of cooling holes are formed, providing a fluid passageway between the interior face and the exterior face of the exterior wall substrate. Each cooling hole is disposed such that it passes through a plateau. A first coating layer is deposited over the exterior face of the exterior wall substrate.
Abstract translation: 公开了一种用于涡轮机的热气路径的部件及其构造方法。 在一个实施例中，所述部件包括外壁基板，其中所述外壁基板包括设置在所述外表面上的内表面和外表面以及多个平台。 形成多个冷却孔，在外壁基材的内表面和外表面之间提供流体通道。 每个冷却孔设置成使其通过平台。 第一涂层沉积在外壁基材的外表面上。
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Patent Agency Ranking
公开(公告)号：US10655477B2
公开(公告)日：2020-05-19
申请号：US15219804
申请日：2016-07-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Joseph Anthony Weber , David Edward Schick
Abstract: Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.
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公开(公告)号：US10590776B2
公开(公告)日：2020-03-17
申请号：US15174332
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
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公开(公告)号：US10570750B2
公开(公告)日：2020-02-25
申请号：US15833431
申请日：2017-12-06
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Gary Michael Itzel
Abstract: A turbine component includes an airfoil having an airfoil chamber disposed within the airfoil, the airfoil chamber configured to supply a coolant through the airfoil. The tip of the airfoil includes a rail extending radially from the tip plate, the rail including an inner rail surface defining a tip pocket therein, an outer rail surface and a radially outward facing rail surface between the inner rail surface and the outer rail surface. A tip rail cavity is within and partially circumscribes the rail, the tip rail cavity receiving a coolant flow. A tip rail cooling passage includes an inlet fluidly coupled to the tip rail cavity, a passage length fluidly coupled to the inlet and partially circumscribing the rail, a metering element fluidly coupled to the passage length, and an outlet fluidly coupled to the metering element and extending through the radially outward facing rail surface.
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公开(公告)号：US20190309634A1
公开(公告)日：2019-10-10
申请号：US15948207
申请日：2018-04-09
Applicant: General Electric Company
Inventor： Gary Michael Itzel , Jeffrey Clarence Jones , James William Vehr
IPC: F01D5/18 , F01D5/28 , B32B3/26 , B33Y80/00 , B29C64/153 , B29C64/393 , B23K26/342
Abstract: An airport having an exterior wall including a plurality of spaced layers for improved cooling and lifetime is disclosed. The airfoil and exterior wall are made by additive manufacturing. The exterior wall includes an exterior layer, an intermediate layer, and an interior layer each separated from adjacent layers by a plurality of standoff members; a plurality of first cooling chambers between the exterior and intermediate layers, the chambers partitioned by a first partitioning wall; a plurality of second cooling chambers between in the intermediate and interior layers, the chambers partitioned by a second partitioning wall; a thermal barrier coating on the exterior layer; a plurality of impingement openings in the intermediate layer and a second plurality of impingement openings in the interior layer; and a plurality of cooling passages in the exterior layer. The exterior layer may also include plateaus on an exterior face through which the cooling passages extend.
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公开(公告)号：US10287894B2
公开(公告)日：2019-05-14
申请号：US15174182
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
IPC: F01D5/18 , B33Y10/00 , B33Y80/00 , B23K26/342 , B23K26/70 , B22F3/105 , B22F3/24 , B23K15/00 , B23K26/00 , C23C28/04 , F01D9/02 , F01D25/12 , F01D5/14 , F01D5/28 , B23K101/00 , B23K103/08
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
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