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    STRUCTURAL GUIDE VANE FOR GAS TURBINE ENGINE
    1.
    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。

    Inserts for slotted integrally bladed rotor
    5.
    发明授权
    Inserts for slotted integrally bladed rotor 有权

    公开(公告)号：US11111804B2

    公开(公告)日：2021-09-07

    申请号：US16298027

    申请日：2019-03-11

    Applicant: United Technologies Corporation

    Inventor： Weston Behling ,  Jason Leroux ,  Robert B. Fuller ,  Steven D. Roberts

    IPC: F01D11/00 ,  F01D5/30

    Abstract: Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

    INSERTS FOR SLOTTED INTEGRALLY BLADED ROTOR
    8.
    发明申请
    INSERTS FOR SLOTTED INTEGRALLY BLADED ROTOR 审中-公开

    公开(公告)号：US20200291802A1

    公开(公告)日：2020-09-17

    申请号：US16298027

    申请日：2019-03-11

    Applicant: United Technologies Corporation

    Inventor： Weston Behling ,  Jason Leroux ,  Robert B. Fuller ,  Steven D. Roberts

    IPC: F01D11/00 ,  F01D5/30

    Abstract: Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

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