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    SOLID SEAL WITH COOLING PATHWAYS
    1.
    发明申请
    SOLID SEAL WITH COOLING PATHWAYS 审中-公开
    固体密封与冷却路径

    公开(公告)号：US20140093353A1

    公开(公告)日：2014-04-03

    申请号：US13633890

    申请日：2012-10-03

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Ibrahim Sezer ,  Randall Richard Good

    IPC: F01D11/00 ,  F01D25/12

    CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D11/006 ,  F01D11/008 ,  F01D25/12 ,  F05D2260/20

    Abstract: The present application provides a seal for use between components facing a high pressure cooling air flow and a hot gas path in a gas turbine engine. The seal may include a first surface facing the high pressure cooling air flow, a second surface with a second surface air plenum facing the hot gas path, and a number of cooling pathways extending from the first surface to the second surface air plenum of the second surface for the high pressure cooling air flow to pass therethrough.

    Abstract translation: 本申请提供了在面向高压冷却空气流的组件和燃气涡轮发动机中的热气体路径之间使用的密封件。 密封件可以包括面向高压冷却空气流的第一表面，具有面向热气体路径的第二表面空气增压室的第二表面和从第一表面延伸到第二表面空气增压室的多个冷却通道 高压冷却空气流通过的表面。

    Interior cooling configurations in turbine rotor blades
    2.
    发明授权
    Interior cooling configurations in turbine rotor blades 有权

    公开(公告)号：US10301945B2

    公开(公告)日：2019-05-28

    申请号：US14974155

    申请日：2015-12-18

    Applicant: General Electric Company

    Inventor： Rohit Chouhan ,  Randall Richard Good ,  Hiteshkumar Rameshchandra Mistry ,  Shashwat Swami Jaiswal

    IPC: F01D5/18 ,  F01D5/20 ,  F01D5/22

    Abstract: A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.

    PLATFORM COOLING OF A TURBINE BLADE ASSEMBLY
    4.
    发明申请
    PLATFORM COOLING OF A TURBINE BLADE ASSEMBLY 审中-公开
    涡轮叶片组件的平台冷却

    公开(公告)号：US20140096538A1

    公开(公告)日：2014-04-10

    申请号：US13646023

    申请日：2012-10-05

    Applicant: General Electric Company

    Inventor： Bradley Taylor Boyer ,  Randall Richard Good

    IPC: F01D5/08

    CPC classification number: F01D5/081 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/205

    Abstract: A turbine blade generally includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform. The platform cooling circuit may extend from the suction side of the platform to the pressure side of the platform. The platform cooling circuit generally defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side.

    Abstract translation: 涡轮叶片通常包括具有压力侧，吸力侧，前缘，后缘，压力侧斜面和吸力侧斜面的平台。 平台冷却电路在平台内延伸。 平台冷却回路可以从平台的吸入侧延伸到平台的压力侧。 平台冷却回路通常限定将冷却介质从平台吸入侧引导到平台压力侧的流体流动路径。

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