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    Selective coating removal or masking for ground path
    22.
    发明授权
    Selective coating removal or masking for ground path 有权
    选择性涂层去除或掩蔽地面路径

    公开(公告)号：US09422821B2

    公开(公告)日：2016-08-23

    申请号：US14776341

    申请日：2014-03-14

    Applicant: United Technologies Corporation

    Inventor： Thomas B. Hyatt ,  Carl Brian Klinetob

    IPC: F01D9/04 ,  F01D5/28 ,  F01D25/24 ,  B64D45/02 ,  F01D25/00

    CPC classification number: F01D9/042 ,  B64D45/02 ,  F01D5/288 ,  F01D25/005 ,  F01D25/243 ,  F05D2220/327 ,  F05D2260/31 ,  F05D2300/17 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/50

    Abstract: A device for providing a grounding path between an outer surface of a gas turbine aircraft engine and an inner surface of a gas turbine aircraft engine uses a structural guide vane (SGV) with a nonconductive coating on the surface. Bolts are put in bolt holes that have a bolt receiving cavity without the nonconductive coating. A washer and bolt are used so that attachment of the SGV to a surface provides a ground path from the SGV through the bolt, washer and nut for electrical engagement with a surface to which the bolt attaches the SGV.

    Abstract translation: 用于在燃气涡轮机飞行器发动机的外表面和燃气涡轮机飞机发动机的内表面之间提供接地路径的装置使用在表面上具有非导电涂层的结构导叶（SGV）。 螺栓被放入螺栓孔中，螺栓孔具有不带非导电涂层的螺栓接收腔。 使用垫圈和螺栓，使得SGV附接到表面提供了从SGV通过螺栓，垫圈和螺母的接地路径，用于与螺栓附接到SGV的表面电接合。

    Gas Turbine Engine Structural Guide Vanes
    23.
    发明申请
    Gas Turbine Engine Structural Guide Vanes 审中-公开
    燃气轮机发动机结构导轨

    公开(公告)号：US20160130958A1

    公开(公告)日：2016-05-12

    申请号：US14919207

    申请日：2015-10-21

    Applicant: United Technologies Corporation

    Inventor： William Richard Ganoe ,  Thomas B. Hyatt

    IPC: F01D9/02 ,  F01D25/00 ,  F02C3/04

    Abstract: A structural guide vane is disclosed. The structural guide vane may include a first root, a second root positioned radially outward from the first root and a truss extending between the first root and second root. The truss may be made of a first material. The guide vane may further include an overmold made of a second material that surrounds the truss to form an airfoil.

    Abstract translation: 公开了结构导叶。 结构导叶可以包括第一根，从第一根径向向外定位的第二根和在第一根和第二根之间延伸的桁架。 桁架可以由第一种材料制成。 引导叶片还可以包括由围绕桁架形成翼型的第二材料制成的包覆模制件。

    STRUCTURAL GUIDE VANE FOR GAS TURBINE ENGINE
    24.
    发明申请
    STRUCTURAL GUIDE VANE FOR GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的结构导向件

    公开(公告)号：US20150361807A1

    公开(公告)日：2015-12-17

    申请号：US14765138

    申请日：2014-03-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Thomas B. Hyatt ,  Carl Brian Klinetob ,  Jason Leroux

    IPC: F01D9/04 ,  F02C7/20 ,  F02C3/04

    CPC classification number: F01D9/04 ,  F01D25/162 ,  F01D25/246 ,  F02C3/04 ,  F02C7/20 ,  Y02T50/671

    Abstract: A guide vane for use in a gas turbine engine fan section has an airfoil extending between a radially inner platform and a radially outer platform. The radially inner platform has a radially outwardly facing surface from which the airfoil extends and a radially inwardly facing underside. The airfoil has a trailing edge extending to a leading edge. The underside is attached to a mount bracket and a main rib extending from the underside of the platform adjacent the trailing edge and in a direction generally towards the leading edge, and merging into a top surface on the mount bracket. A pair of shoulders is formed on each of two circumferential sides of the rib. Each of the shoulders is spaced from each other at a point on the shoulders connected into the top surface of the mount bracket. The shoulders extend circumferentially toward each other and the under surface.

    Abstract translation: 用于燃气涡轮发动机风扇部分的导向叶片具有在径向内部平台和径向外部平台之间延伸的翼型件。 径向内部平台具有径向向外的表面，翼面从该表面延伸并且径向向内面向下。 翼型件具有延伸到前缘的后缘。 下侧附接到安装支架和从平台的下侧延伸的主肋邻近后缘并且大致朝向前缘的方向，并且合并到安装支架上的顶表面中。 在肋的两个圆周侧的每一个上形成一对肩部。 每个肩部在连接到安装支架顶表面的肩部上的一个点处彼此间隔开。 肩部朝向彼此和下表面周向延伸。

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