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    Adaptively opening backup cooling pathway
    1.
    发明授权
    Adaptively opening backup cooling pathway 有权

    公开(公告)号：US10760430B2

    公开(公告)日：2020-09-01

    申请号：US15609598

    申请日：2017-05-31

    Applicant: General Electric Company

    Inventor： Benjamin Paul Lacy ,  Brian Peter Arness ,  Victor John Morgan ,  Stephen William Tesh

    IPC: F01D5/08 ,  F01D5/18 ,  F01D9/04 ,  F01D9/06

    Abstract: A hot gas path (HGP) component of an industrial machine includes primary and secondary cooling pathways. A body includes an internal cooling circuit carrying a cooling medium. A primary cooling pathway is spaced internally in the body and carries a primary flow of a cooling medium from an internal cooling circuit. A secondary cooling pathway is in the body and in fluid communication with an internal cooling circuit. The secondary cooling pathway is fluidly incommunicative and spaced internally from the primary cooling pathway. In response to an overheating event occurring, the secondary cooling pathway opens to allow a secondary flow of cooling medium through to the outer surface of the body and/or the primary cooling pathway. The primary flow flows in the primary cooling pathway prior to the overheating event, and the secondary flow of cooling medium does not flow until after an opening of the secondary cooling pathway.

    Systems and methods for assembling flow path components
    2.
    发明授权
    Systems and methods for assembling flow path components 有权

    公开(公告)号：US10655489B2

    公开(公告)日：2020-05-19

    申请号：US15862520

    申请日：2018-01-04

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Neelesh Nandkumar Sarawate ,  Christopher Edward Wolfe ,  Victor John Morgan ,  Jason Ray Gregg

    IPC: F01D11/00 ,  F01D9/04

    Abstract: An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.

    Hot gas path component for turbine system
    3.
    发明授权
    Hot gas path component for turbine system 有权

    公开(公告)号：US10100666B2

    公开(公告)日：2018-10-16

    申请号：US13853556

    申请日：2013-03-29

    Applicant: General Electric Company

    Inventor： Brian Gene Brzek ,  Victor John Morgan ,  Benjamin Paul Lacy

    IPC: F01D25/12 ,  F01D5/14 ,  F01D9/02 ,  F01D5/18 ,  F01D9/04

    Abstract: A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough.

    COOLING STRUCTURE FOR HOT-GAS PATH COMPONENTS WITH METHODS OF FABRICATION
    5.
    发明申请
    COOLING STRUCTURE FOR HOT-GAS PATH COMPONENTS WITH METHODS OF FABRICATION 有权
    具有制造方法的热气路径组件的冷却结构

    公开(公告)号：US20170037731A1

    公开(公告)日：2017-02-09

    申请号：US14818695

    申请日：2015-08-05

    Applicant: General Electric Company

    Inventor： Victor John Morgan ,  George Andrew Gergely ,  Frederic Woodrow Roberts, JR. ,  Aaron Ezekiel Smith

    IPC: F01D5/18 ,  B23P15/02 ,  F01D9/06

    CPC classification number: F01D5/187 ,  B23P15/02 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/314 ,  F05D2250/75 ,  F05D2260/2212 ,  F05D2260/2214

    Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.

    Abstract translation: 本公开的实施例提供了用于热气路径（HGP）部件的部件及其形成方法。 根据本公开的结构可以包括：HGP部件，其从涡轮机的转子轴线径向延伸，所述HGP部件包括锥形边缘; 多个第一通道，其与HGP部件的预冷却区域流体连通，并且延伸穿过位于预冷却区域和锥形边缘之间的侧壁; 以及多个第二通道，其至少延伸穿过所述锥形边缘，其中所述多个第二通道中的每一个与所述操作流体的流动路径和所述多个第一通道的至少一个通道流体连通，并且其中至少 多个第二通道中的一个从多个第一通道的每个通道径向移位。

    FLEXIBLE LAYERED SEAL FOR TURBOMACHINERY
    7.
    发明申请
    FLEXIBLE LAYERED SEAL FOR TURBOMACHINERY 审中-公开
    柔性层封装用于涡轮机

    公开(公告)号：US20160024951A1

    公开(公告)日：2016-01-28

    申请号：US14337453

    申请日：2014-07-22

    Applicant: General Electric Company

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

    IPC: F01D11/00 ,  F16J15/02

    CPC classification number: F01D11/005 ,  F05D2240/59 ,  F16J15/02 ,  F16J15/0812

    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.

    Abstract translation: 本申请提供了具有改进的柔性的密封组件，用于减少涡轮机械的相邻不对准部件之间的泄漏。 密封组件包括由柔性可渗透材料形成的第一外垫片和由基本上不可渗透的材料形成的第二外垫片。 至少第二外垫片构造成用于与相邻部件的密封槽密封接合。 密封组件还可以包括位于第一和第二外垫片之间的内垫片和填料层中的至少一个。 密封组件可以足够灵活以考虑相邻部件之间的不对准，足够坚硬以满足组装要求，并且足够坚固以满足与涡轮机械相关的操作要求。 提供包括密封组件的涡轮机。

    METHOD AND SYSTEM FOR PROVIDING SEALING IN GAS TURBINES
    8.
    发明申请
    METHOD AND SYSTEM FOR PROVIDING SEALING IN GAS TURBINES 审中-公开
    用于在气体涡轮机中提供密封的方法和系统

    公开(公告)号：US20150118042A1

    公开(公告)日：2015-04-30

    申请号：US14063269

    申请日：2013-10-25

    Applicant: General Electric Company

    Inventor： Victor John Morgan ,  Aaron Ezekiel Smith ,  David Wayne Weber

    IPC: F01D11/00

    CPC classification number: F01D11/005 ,  F01D11/003 ,  F01D11/006 ,  F01D11/008

    Abstract: A gas turbine system is provided that includes a compressor section, a combustor assembly coupled to the compressor section, and a turbine section coupled to the compressor section. At least one of the combustor assembly and the turbine section includes a sealing sub-system for use in sealing between a first component and a second component. A first component defines a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region. A second component adjacent the first component defines a second seal member receiving region oriented adjacent the first seal member receiving region. The sealing system includes first and second end walls defined in at least one of the first and second seal member receiving regions. A seal member is oriented within the first and second seal member receiving regions, and includes at least a first layer defining at least a first resilient seal end portion that engages one of the first and second end walls.

    Abstract translation: 提供了一种燃气轮机系统，其包括压缩机部分，联接到压缩机部分的燃烧器组件和联接到压缩机部分的涡轮部分。 燃烧器组件和涡轮部分中的至少一个包括用于密封第一部件和第二部件之间的密封子系统。 第一部件限定在较高温度气体区域和较冷温度气体区域之间定向的第一密封构件接收区域。 与第一部件相邻的第二部件限定了邻近第一密封件接收区域定向的第二密封件接收区域。 密封系统包括限定在第一和第二密封构件接收区域中的至少一个中的第一和第二端壁。 密封构件定位在第一和第二密封构件接收区域内，并且包括限定至少第一弹性密封端部的至少第一层，该第一层限定第一和第二端壁中的一个。

    TURBINE COMPONENTS WITH PASSIVE COOLING PATHWAYS
    10.
    发明申请
    TURBINE COMPONENTS WITH PASSIVE COOLING PATHWAYS 有权
    涡轮组件与无源冷却路径

    公开(公告)号：US20140099183A1

    公开(公告)日：2014-04-10

    申请号：US13645729

    申请日：2012-10-05

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Victor John Morgan ,  Stephen Gerard Pope ,  Jacob Kittleson ,  Lawrence Matthew Levy

    IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02

    CPC classification number: F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F05D2230/10 ,  F05D2230/50 ,  F05D2300/611

    Abstract: The present application provides a turbine component for use in a hot gas path of a gas turbine. The turbine component may include an outer surface, an internal cooling circuit, a number of cooling pathways in communication with the internal cooling circuit and extending through the outer surface, and a number of adaptive cooling pathways in communication with the internal cooling circuit and extending through the outer surface. The adaptive cooling pathways may include a high temperature compound therein.

    Abstract translation: 本申请提供了一种在燃气轮机的热气路径中使用的涡轮机部件。 涡轮机部件可以包括外表面，内部冷却回路，与内部冷却回路连通并延伸穿过外表面的多个冷却通路，以及与内部冷却回路连通并延伸通过的多个自适应冷却通道 外表面。 适应性冷却途径可包括其中的高温化合物。

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