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    TURBINE COMPONENT INTERNAL HEATING SYSTEMS AND COATING SYSTEMS
    1.
    发明申请
    TURBINE COMPONENT INTERNAL HEATING SYSTEMS AND COATING SYSTEMS 审中-公开
    涡轮组件内部加热系统和涂层系统

    公开(公告)号：US20150307978A1

    公开(公告)日：2015-10-29

    申请号：US14264190

    申请日：2014-04-29

    Applicant: General Electric Company

    Inventor： Lawrence Matthew Levy ,  Ronald Lee Souther

    IPC: C23C4/02 ,  H05B3/00 ,  H05B6/10

    CPC classification number: C23C4/02 ,  B05B12/12 ,  B05B12/20 ,  B05B13/02 ,  B05D3/0218 ,  B05D2202/00 ,  C23C4/12 ,  F01D5/288 ,  F01D25/285 ,  F05D2230/90 ,  H05B3/0061 ,  H05B6/101 ,  Y02T50/6765

    Abstract: Turbine component internal heating systems include at least one turbine component support platform that supports a turbine component having one or more internal cavities by temporarily engaging at least a side wall of the turbine component, and, at least one heat source that extends from the at least one turbine component support platform, wherein when the at least one turbine component support platform supports the turbine component, the at least one heat source is at least partially disposed within at least one of the one or more internal cavities such that it can heat the turbine component from the inside.

    Abstract translation: 涡轮机部件内部加热系统包括至少一个涡轮机部件支撑平台，该涡轮机部件支撑平台通过临时接合涡轮机部件的至少一个侧壁来支撑具有一个或多个内部空腔的涡轮机部件，以及至少一个从至少一个 一个涡轮机部件支撑平台，其中当所述至少一个涡轮机部件支撑平台支撑所述涡轮机部件时，所述至少一个热源至少部分地设置在所述一个或多个内部空腔中的至少一个内部空腔中，使得其可以加热所述涡轮机 组件从里面。

    SYSTEM FOR CHECKING CALIBRATION OF A ROBOTIC MULTI-AXIS MACHINE
    3.
    发明申请
    SYSTEM FOR CHECKING CALIBRATION OF A ROBOTIC MULTI-AXIS MACHINE 审中-公开

    公开(公告)号：US20170095929A1

    公开(公告)日：2017-04-06

    申请号：US14876027

    申请日：2015-10-06

    Applicant: General Electric Company

    Inventor： Lawrence Matthew Levy ,  Jon E. Dickinson ,  Patrick Thomas Walsh

    IPC: B25J9/16

    CPC classification number: B25J9/1692 ,  G05B2219/39033 ,  G05B2219/39045

    Abstract: A system for checking calibration of a multi-axis machine includes a robotic arm and a mount configured to receive a removable machine tool and a controller electronically connected to the multi-axis machine. The removable machine tool includes a removable spray nozzle and a laser housing that is coupled to the machine tool. The laser housing includes a laser affixed inside the housing for emitting a laser beam and a calibration workpiece coupled to a mounting table. The calibration workpiece comprises a plurality of laser sensors disposed along an outer surface of the calibration workpiece. The controller is programmed to point the laser beam at each laser sensor. The laser sensors generate signals that are communicated back to the controller if the laser beam is detected by the laser sensor.

    TURBINE COMPONENTS WITH PASSIVE COOLING PATHWAYS
    4.
    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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