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    EXPANSION SEAL
    1.
    发明申请
    EXPANSION SEAL 审中-公开

    公开(公告)号：US20170097096A1

    公开(公告)日：2017-04-06

    申请号：US14872640

    申请日：2015-10-01

    Applicant: United Technologies Corporation

    Inventor： Philip Robert Rioux

    IPC: F16J15/40 ,  F01D9/04 ,  F01D11/02

    CPC classification number: F16J15/40 ,  F01D9/041 ,  F01D11/005 ,  F01D11/025 ,  F05D2220/32 ,  F05D2240/55

    Abstract: A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal.

    Blast shield for high pressure compressor
    5.
    发明授权
    Blast shield for high pressure compressor 有权
    高压压缩机防爆罩

    公开(公告)号：US09322415B2

    公开(公告)日：2016-04-26

    申请号：US13662900

    申请日：2012-10-29

    Applicant: United Technologies Corporation

    Inventor： Philip Robert Rioux

    IPC: F01D11/18 ,  F04D29/58 ,  F04D19/02 ,  F04D29/54 ,  F01D25/24

    CPC classification number: F04D29/5853 ,  F01D11/18 ,  F01D25/246 ,  F04D19/02 ,  F04D29/542 ,  F05D2240/15 ,  Y02T50/671

    Abstract: A high pressure compressor includes an inner case wall, a plurality of flanges extending outwardly from the inner case wall, a shield that surrounds at least a portion of at least one of the plurality of flanges to define a chamber that at least partially encases at least one of the plurality of flanges, and a passage at least partially defined by the shield that allows air to circulate into the chamber.

    Abstract translation: 高压压缩机包括内壳壁，从内壳壁向外延伸的多个凸缘，围绕多个凸缘中的至少一个凸缘的至少一部分的屏蔽件，以限定至少部分地至少部分地封闭的腔室 多个凸缘中的一个，以及至少部分地由屏蔽件限定的通道，其允许空气循环进入腔室。

    EXPANSION SEAL
    6.
    发明申请
    EXPANSION SEAL 审中-公开

    公开(公告)号：US20200056703A1

    公开(公告)日：2020-02-20

    申请号：US16600073

    申请日：2019-10-11

    Applicant: United Technologies Corporation

    Inventor： Philip Robert Rioux

    IPC: F16J15/40 ,  F01D11/02 ,  F01D9/04 ,  F01D11/00

    Abstract: A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal.

    Shroud seal and wearliner
    8.
    发明授权
    Shroud seal and wearliner 有权

    公开(公告)号：US10107125B2

    公开(公告)日：2018-10-23

    申请号：US14943749

    申请日：2015-11-17

    Applicant: United Technologies Corporation

    Inventor： Philip Robert Rioux

    IPC: F01D11/00 ,  F04D9/04 ,  F01D9/04

    Abstract: A stator assembly includes a first stator vane sub-assembly with a first platform and a first airfoil extending from the first platform, and a second stator vane sub-assembly with a second platform and a second airfoil extending from the second platform. A gap is defined circumferentially between the first stator vane sub-assembly and the second stator vane sub-assembly. The stator assembly also includes a shroud structure, a first chamber defined between the first platform and the shroud structure, a second chamber defined between the second platform and the shroud structure, and a damper spring seal structure. Also included is a plate having a first portion within the first chamber and a second portion within the second chamber, such that the plate extends from the first chamber across the gap to the second chamber.

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