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    TURBINE ENGINE GEARBOX MOUNT WITH MULTIPLE FUSE JOINTS
    11.
    发明申请
    TURBINE ENGINE GEARBOX MOUNT WITH MULTIPLE FUSE JOINTS 有权
    涡轮发动机齿轮箱安装多个保险丝接头

    公开(公告)号：US20140314546A1

    公开(公告)日：2014-10-23

    申请号：US13726133

    申请日：2012-12-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Todd A. Davis ,  Timothy Webb ,  Mark Ronski

    IPC: F02C7/36

    CPC classification number: F02C7/36 ,  F01D21/045 ,  F02C7/32 ,  F05D2260/311 ,  Y02T50/671

    Abstract: A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts.

    Abstract translation: 涡轮发动机组件包括涡轮发动机壳体，齿轮箱和将齿轮箱连接到壳体的多个安装件。 每个安装件包括连接件和保险丝接头。 连接件基本上沿着第一方向朝向壳体延伸。 保险丝接头被构造成基本上防止当保险丝接头承受小于阈值时的变速箱和壳体之间的运动，并且当负载大于阈值时允许齿轮箱与壳体之间的受限运动。 第一座架的保险丝接头具有与第二座架的保险丝接头不同的构造。

    Unified curved beam bearing damper
    15.
    发明授权
    Unified curved beam bearing damper 有权

    公开(公告)号：US11035252B2

    公开(公告)日：2021-06-15

    申请号：US16668684

    申请日：2019-10-30

    Applicant: United Technologies Corporation

    Inventor： Todd A. Davis ,  Russell B. Witlicki ,  Christopher M. Valva ,  Andrew Newton ,  David C. Kiely

    IPC: F01D25/16 ,  F16C27/04 ,  F16C19/00

    Abstract: A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.

    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    18.
    发明申请
    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 审中-公开

    公开(公告)号：US20200025030A1

    公开(公告)日：2020-01-23

    申请号：US16286970

    申请日：2019-02-27

    Applicant: United Technologies Corporation

    Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Todd A. Davis ,  Gregory E. Reinhardt ,  Enzo DiBenedetto

    IPC: F01D25/16 ,  F02C7/36 ,  F02K3/04 ,  F02C7/06

    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.

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