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    GAS TURBINE ENGINE NOSE CONE ATTACHMENT CONFIGURATION
    12.
    发明申请
    GAS TURBINE ENGINE NOSE CONE ATTACHMENT CONFIGURATION 有权
    气体发动机发动机气缸附件配置

    公开(公告)号：US20140199176A1

    公开(公告)日：2014-07-17

    申请号：US13739294

    申请日：2013-01-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Peter V. Tomeo ,  Carney R. Anderson

    IPC: F01D5/02 ,  B23P15/04

    CPC classification number: B23P15/04 ,  F01D5/025 ,  F01D5/282 ,  F01D11/008 ,  F02C7/04 ,  F05D2220/3216 ,  F05D2220/36 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49327

    Abstract: A gas turbine engine fan section includes a fan hub configured to rotate about an axis. A nose cone includes a spinner operatively mounted to the fan hub. The spinner supports a first fastening element and the nose cone includes an annular cover arranged over the fastening element. The spinner and annular cover provide an aerodynamic exterior surface of the nose cone without exposed fasteners. A second fastening element cooperates with the first fastening element to secure the spinner relative to the fan hub. The first and second fastening elements are oriented transversely to the axis.

    Abstract translation: 燃气涡轮发动机风扇部分包括构造成围绕轴线旋转的风扇毂。 鼻锥包括可操作地安装到风扇毂的旋转器。 旋转器支撑第一紧固元件，并且鼻锥包括布置在紧固元件上方的环形盖。 旋转器和环形盖提供鼻锥体的空气动力学外表面，而不会暴露紧固件。 第二紧固元件与第一紧固元件配合以相对于风扇毂固定旋转器。 第一和第二紧固元件横向于轴线定向。

    Bladed rotor disk including anti-vibratory feature
    13.
    发明授权
    Bladed rotor disk including anti-vibratory feature 有权

    公开(公告)号：US10066502B2

    公开(公告)日：2018-09-04

    申请号：US14918923

    申请日：2015-10-21

    Applicant: United Technologies Corporation

    Inventor： Carney R. Anderson

    IPC: F01D25/06 ,  F01D5/30 ,  F01D5/02 ,  F01D5/10

    Abstract: A rotor disk includes a ring shaped rotor body defining a radially inward opening, rims protrude radially outward from the rotor body, and outwardly facing rotor blade retention slots are defined between circumferentially adjacent rims. Each slot is operable to receive and retain a corresponding rotor blade, and each rim of the rims includes an anti-vibratory feature. The anti-vibratory feature includes a structure defining an isogrid pattern intruding into a surface of the rim.

    Gas turbine engine fan blade lock assembly
    15.
    发明授权
    Gas turbine engine fan blade lock assembly 有权
    燃气涡轮发动机风扇叶片锁组件

    公开(公告)号：US09376926B2

    公开(公告)日：2016-06-28

    申请号：US13677470

    申请日：2012-11-15

    Applicant: United Technologies Corporation

    Inventor： Carney R. Anderson ,  Peter V. Tomeo

    IPC: F01D5/30 ,  F01D5/32

    CPC classification number: F01D5/3015 ,  F01D5/323 ,  Y02T50/673

    Abstract: A gas turbine engine fan blade lock assembly includes a fan hub that has blade slots each configured to receive a root of a fan blade. The fan hub includes circumferentially spaced first slots. A lock ring is configured to move between unlocked and locked positions. The lock ring includes circumferentially spaced second slots aligned with the first slots in the locked position, and multiple discrete pins. Each pin is configured to be slidably received in paired first and second slots in the locked position to prevent rotational movement of the lock ring relative the fan hub.

    Abstract translation: 燃气涡轮发动机风扇叶片锁定组件包括风扇毂，其具有各自被配置为接收风扇叶片的根部的叶片槽。 风扇毂包括周向间隔开的第一槽。 锁定环配置为在未锁定位置和锁定位置之间移动。 锁定环包括在锁定位置与第一槽对准的周向间隔开的第二槽和多个分立的销。 每个销被构造成在锁定位置可滑动地容纳在成对的第一和第二槽中，以防止锁环相对于风扇毂的旋转运动。

    Gas turbine engine rotor seal
    17.
    发明授权
    Gas turbine engine rotor seal 有权
    燃气轮机发动机转子密封

    公开(公告)号：US09169737B2

    公开(公告)日：2015-10-27

    申请号：US13671205

    申请日：2012-11-07

    Applicant: United Technologies Corporation

    Inventor： Nicholas Aiello ,  Carney R. Anderson

    IPC: F01D11/00

    CPC classification number: F01D11/001

    Abstract: A rotary seal for sealing a bladed rotor of a gas turbine engine to a stator thereof comprises a sealing element and a sealing element support comprising a radially outer edge portion on which the sealing element is fixed, a radially inner mounting portion adapted to be attached to a supported rotor hub, and a flexible, medial web portion extending between the radially outer edge portion and the radially inner mounting portion.

    Abstract translation: 用于将燃气涡轮发动机的叶片转子密封到其定子的旋转密封件包括密封元件和密封元件支撑件，所述密封元件和密封元件支撑件包括固定密封元件的径向外边缘部分，适于附接到 支撑的转子轮毂和在径向外边缘部分和径向内部安装部分之间延伸的柔性内侧腹板部分。

    Aircraft blade lock retainer
    19.
    发明授权
    Aircraft blade lock retainer 有权

    公开(公告)号：US10132174B2

    公开(公告)日：2018-11-20

    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 ,  F01D5/30 ,  F02K7/06

    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.

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