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    CONJOINED GAS TURBINE INTERFACE SEAL
    53.
    发明申请
    CONJOINED GAS TURBINE INTERFACE SEAL 审中-公开
    连续气体涡街界面密封

    公开(公告)号：US20140348642A1

    公开(公告)日：2014-11-27

    申请号：US13875370

    申请日：2013-05-02

    Applicant: General Electric Company

    Inventor： David Wayne Weber ,  Victor John Morgan ,  Neelesh Nandkumar Sarawate

    IPC: F01D11/00 ,  F01D11/24

    CPC classification number: F01D11/005 ,  F05D2240/11 ,  F05D2240/59 ,  F05D2250/75

    Abstract: A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer.

    Abstract translation: 公开了一种包括用于减少燃气涡轮机中的间隙间隙（例如，成角度间隙，“L'形间隙等”）泄漏的结合层压体界面密封件的装置。 在一个实施例中，一种用于燃气涡轮机的密封装置包括：第一凸缘，其被成形为设置在第一弓形部件的第一槽内和第二弧形部件的第一相邻狭槽内; 连接到所述第一凸缘的第一表面的连接层，所述第一表面被配置为面对所述燃气轮机的工作流体流; 以及第二凸缘，其被成形为设置在所述第一弓形部件的第二狭槽内以及所述第二弓形部件的第二相邻狭槽中，所述第二凸缘包括连接到所述连结层的第二表面。

    SPLINE SEAL WITH COOLING PATHWAYS
    54.
    发明申请
    SPLINE SEAL WITH COOLING PATHWAYS 审中-公开
    带冷却通道的SPACE密封

    公开(公告)号：US20140091531A1

    公开(公告)日：2014-04-03

    申请号：US13633891

    申请日：2012-10-03

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Victor John Morgan ,  David Wayne Weber

    IPC: F02C7/18 ,  F02C7/28

    CPC classification number: F01D11/005 ,  F01D25/12 ,  F05D2240/55 ,  F05D2260/20 ,  F16J15/027 ,  F16J15/0812 ,  F16J15/0825

    Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.

    Abstract translation: 本申请提供了在面向高压冷却空气流的部件发动机和燃气涡轮机中的热气体路径之间使用的密封件。 密封件可以包括第一垫片，具有空气出口孔的第二垫片，位于第一垫片和第二垫片之间的一个或多个中间层，以及延伸穿过用于高压冷却空气流的中间层的一个或多个冷却路径 通过空气出口孔流入热气路径。

    Unitary body turbine shrouds including internal cooling passages
    56.
    发明授权
    Unitary body turbine shrouds including internal cooling passages 有权

    公开(公告)号：US10822986B2

    公开(公告)日：2020-11-03

    申请号：US16263548

    申请日：2019-01-31

    Applicant: General Electric Company

    Inventor： Zachary John Snider ,  David Wayne Weber

    IPC: F01D11/08 ,  F01D25/12

    Abstract: Turbine shrouds including internal cooling passages are disclosed. The shrouds may include a unitary body including a support portion, an intermediate portion formed integral with and extending from the support portion, and a seal portion formed integral with the intermediate portion, opposite the support portion. The unitary body may also include two opposing slash faces extending between the support portion and the seal portion, a HGP seal slot formed on each of the two opposing slash faces, and at least one plenum and cooling passage extending through the support portion, intermediate portion, and/or the seal portion. The unitary body may also include an exhaust channel and slash face exhaust holes formed in each of the two opposing slash faces. The exhaust channel may be in fluid communication with the cooling passage(s), and the slash face exhaust holes may be in fluid communication with the exhaust channel.

    UNITARY BODY TURBINE SHROUDS INCLUDING INTERNAL COOLING PASSAGES
    59.
    发明申请
    UNITARY BODY TURBINE SHROUDS INCLUDING INTERNAL COOLING PASSAGES 审中-公开

    公开(公告)号：US20200248558A1

    公开(公告)日：2020-08-06

    申请号：US16263548

    申请日：2019-01-31

    Applicant: General Electric Company

    Inventor： Zachary John Snider ,  David Wayne Weber

    IPC: F01D5/14 ,  F01D25/14 ,  F01D5/20 ,  F01D11/08

    Abstract: Turbine shrouds including internal cooling passages are disclosed. The shrouds may include a unitary body including a support portion, an intermediate portion formed integral with and extending from the support portion, and a seal portion formed integral with the intermediate portion, opposite the support portion. The unitary body may also include two opposing slash faces extending between the support portion and the seal portion, a HGP seal slot formed on each of the two opposing slash faces, and at least one plenum and cooling passage extending through the support portion, intermediate portion, and/or the seal portion. The unitary body may also include an exhaust channel and slash face exhaust holes formed in each of the two opposing slash faces. The exhaust channel may be in fluid communication with the cooling passage(s), and the slash face exhaust holes may be in fluid communication with the exhaust channel.

    Edge coupon including cooling circuit for airfoil
    60.
    发明授权
    Edge coupon including cooling circuit for airfoil 有权

    公开(公告)号：US10598028B2

    公开(公告)日：2020-03-24

    申请号：US15334471

    申请日：2016-10-26

    Applicant: General Electric Company

    Inventor： Robert Frank Hoskin ,  David Wayne Weber ,  Gregory Thomas Foster

    IPC: F01D5/18 ,  F01D5/14

    Abstract: An edge coupon for an airfoil is provided. The coupon includes: a coupon body including: a coolant feed; an outward leg extending toward an edge of the coupon and fluidly coupled to the coolant feed; a return leg extending away from the edge of the coupon and radially offset from the outward leg along a radial axis of the coupon; a turn for fluidly coupling the outward leg and the return leg; a collection passage fluidly coupled to the return leg; and a coupling region configured to mate with an airfoil body of the airfoil.

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