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    AIRCRAFT BLADE LOCK RETAINER
    32.
    发明申请
    AIRCRAFT BLADE LOCK RETAINER 审中-公开
    飞机叶片锁定器

    公开(公告)号：US20160298469A1

    公开(公告)日：2016-10-13

    申请号：US14685030

    申请日：2015-04-13

    Applicant: United Technologies Corporation

    Inventor： Colin J. Kling ,  Thomas J. Robertson ,  Carney R. Anderson ,  James J. McPhail

    IPC: F01D5/32 ,  F01D5/28

    CPC classification number: F01D5/326 ,  F01D5/282 ,  F01D5/3015 ,  F01D5/3076 ,  F02K7/06 ,  F05D2220/36 ,  F05D2230/54 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/603 ,  Y02T50/672

    Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.

    Abstract translation: 本公开提供了与飞机发动机风扇组件和叶片锁定保持器相关的装置。 在各种实施例中，刀片锁定保持器由金属板形成并且包括环形环部分，外部保持器突出部分和内部突出部分。 在各种实施例中，外保持器突片部分设置在环形环部分的外圆周上，该圆环部分的外圆周基本上垂直于环形环部分，并且从环形环部分沿向后的方向延伸。 在各种实施例中，内部保持器突出部分设置在环形环部分的内圆周上并且与外部保持器突片部分径向对准，该外部保持器突出部分基本上垂直于环形环部分定向，并且从环形环部分向前方向延伸 。

    BONDED MOUNT RING SPINNER
    33.
    发明申请
    BONDED MOUNT RING SPINNER 审中-公开
    绑定安装环锭子

    公开(公告)号：US20160288902A1

    公开(公告)日：2016-10-06

    申请号：US15030787

    申请日：2014-05-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Colin J. Kling ,  Scot A. Webb ,  James J. McPhail

    IPC: B64C11/14 ,  F02C3/04

    CPC classification number: B64C11/14 ,  F01D5/066 ,  F02C3/04 ,  F05D2220/36 ,  F05D2230/23 ,  Y02T50/672

    Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.

    Abstract translation: 公开了一种燃气涡轮发动机的风扇组件，用于制造燃气涡轮发动机的风扇组件的方法和燃气涡轮发动机。 燃气涡轮发动机的风扇组件可以包括旋转器部分，旋转器部分的后部的风扇毂部分以及它们之间的接头。 风扇组件还可以包括用于内部支撑旋转器的支撑环，支撑环包括面向风扇毂的第一部分和在接头处连接到旋转器的第二部分，其中第二部分和关节之间的连接是 绑定连接。

    Fan platform wedge seal
    36.
    发明授权
    Fan platform wedge seal 有权

    公开(公告)号：US11028714B2

    公开(公告)日：2021-06-08

    申请号：US16036038

    申请日：2018-07-16

    Applicant: United Technologies Corporation

    Inventor： Colin J. Kling

    IPC: F01D11/00 ,  F01D5/02 ,  F01D5/30 ,  F04D29/32 ,  F02C7/36

    Abstract: A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.

    Nosecap
    39.
    发明授权
    Nosecap 有权

    公开(公告)号：US10352236B2

    公开(公告)日：2019-07-16

    申请号：US15032517

    申请日：2014-10-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Colin J. Kling ,  Charles W. Brown

    IPC: F02C7/04 ,  B29C45/00 ,  B64C11/14

    Abstract: The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment. The nosecap may have bolt holes surrounded by bolt pockets that are asymmetric about a plane passing through a geometric center of the nosecap and passing through and dividing the bolt hole in an embodiment.

    Toroidal spinner aft flange
    40.
    发明授权
    Toroidal spinner aft flange 有权

    公开(公告)号：US10343765B2

    公开(公告)日：2019-07-09

    申请号：US15171926

    申请日：2016-06-02

    Applicant: United Technologies Corporation

    Inventor： James J. McPhail ,  Colin J. Kling

    IPC: F02C7/04 ,  B64C11/14 ,  F02K3/06

    Abstract: A spinner for a gas turbine engine may include a substantially-flat inner surface having frustoconical geometry. A flange having semi-toroidal geometry may extend from the spinner with an inner curved surface of the flange being tangential to the inner surface. A mating portion may extend substantially tangentially from the inner curved surface of the flange and configured for fastening to a fan hub.

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