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    RADIAL PINCH BOLT HEAD SEAL
    22.
    发明申请
    RADIAL PINCH BOLT HEAD SEAL 审中-公开

    公开(公告)号：US20160327082A1

    公开(公告)日：2016-11-10

    申请号：US14706636

    申请日：2015-05-07

    Applicant: United Technologies Corporation

    Inventor： Justin J. Phillips ,  Todd A. Davis

    IPC: F16B33/00

    CPC classification number: F16B33/004 ,  F01D11/005 ,  F01D25/243 ,  F05D2260/31

    Abstract: Aspects of the disclosure are directed to an assembly associated with an engine of an aircraft, comprising a bolt comprising at least one groove, and at least one seal seated within the at least one groove, where the at least one seal is configured to seal radially against a counter bore that the bolt is coupled to. Aspects of the disclosure are directed to a bolt comprising a head, a first groove formed in a first side of the head and configured to seat a first seal, and an internal feature formed in the head and interfacing with a surface of the head, where the internal feature is configured to enable the bolt to be tightened.

    Abstract translation: 本公开的方面涉及与飞机的发动机相关联的组件，包括至少一个凹槽的螺栓和位于至少一个凹槽内的至少一个密封件，其中所述至少一个密封件构造成径向地密封 抵靠螺栓连接的反向孔。 本公开的方面涉及一种螺栓，其包括头部，形成在头部的第一侧中并构造成安置第一密封件的第一凹槽以及形成在头部中并与头部表面相接合的内部特征， 内部功能被配置为使螺栓能够拧紧。

    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION
    25.
    发明申请
    GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION 审中-公开
    气体涡轮发动机轴承轴承配置

    公开(公告)号：US20140230403A1

    公开(公告)日：2014-08-21

    申请号：US14012576

    申请日：2013-08-28

    Applicant: United Technologies Corporation

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

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

    CPC classification number: F01D25/162 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F02K3/04 ,  Y02T50/671

    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.

    Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 第一轴支撑轴向设置在入口壳体流动路径和中间壳体流动路径之间的低压压缩机部分。 第一轴承相对于入口壳体支撑第一轴。 第二轴承相对于中间壳体支撑第二轴。 低压压缩机毂安装在第一轴上。 低压压缩机毂在第一轴承和第二轴承之间延伸到低压压缩机部分。

    Compliant jumper tube fitting
    28.
    发明授权
    Compliant jumper tube fitting 有权

    公开(公告)号：US11371632B2

    公开(公告)日：2022-06-28

    申请号：US16521122

    申请日：2019-07-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Todd A. Davis ,  Brad E. Fiore

    IPC: F16L27/02 ,  F01D9/06 ,  F02C7/06

    Abstract: A compliant jumper tube fitting assembly may comprise an outer housing comprising a first annular cylindrical structure including a first opening defined by a base wall, and an inner housing comprising a second annular cylindrical structure including a second opening defined by an annular wall, wherein the inner housing is configured to generate a seal between an inner diameter wall of the outer housing and an outer diameter wall of the inner housing in response to inserting the inner housing into a mouth end of the outer housing, wherein the inner housing is configured to receive an end fitting and generate a seal between an inner diameter wall of the inner housing in response to inserting the end fitting into the inner housing.

    AXIALLY RIGID CURVED BEAM WITH SQUEEZE DAMPER
    29.
    发明申请
    AXIALLY RIGID CURVED BEAM WITH SQUEEZE DAMPER 有权

    公开(公告)号：US20210131304A1

    公开(公告)日：2021-05-06

    申请号：US16668786

    申请日：2019-10-30

    Applicant: United Technologies Corporation

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

    IPC: F01D25/04

    Abstract: A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.

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