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    Compliant seal assembly and method of operating
    1.
    发明授权
    Compliant seal assembly and method of operating 有权

    公开(公告)号：US10570766B2

    公开(公告)日：2020-02-25

    申请号：US16033746

    申请日：2018-07-12

    Applicant: United Technologies Corporation

    Inventor： Jonathan Lemoine ,  Steven D. Porter

    IPC: F01D11/00 ,  F16J15/44 ,  F16J9/12 ,  F16J15/56 ,  F02C7/28 ,  F16J15/16

    Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.

    ORIENTATION FEATURE FOR SWIRLER TUBE
    2.
    发明申请
    ORIENTATION FEATURE FOR SWIRLER TUBE 审中-公开
    SWIRLER TUBE的定位功能

    公开(公告)号：US20160230666A1

    公开(公告)日：2016-08-11

    申请号：US14617109

    申请日：2015-02-09

    Applicant: United Technologies Corporation

    Inventor： Kevin Zacchera ,  Matthew Andrew Hough ,  Jonathan Lemoine ,  Christopher Treat ,  Alberto A. Mateo

    IPC: F02C7/20 ,  F02C7/12

    CPC classification number: F02C7/20 ,  F01D5/081 ,  F02C7/12 ,  F05D2230/64 ,  F05D2260/14 ,  F05D2260/30 ,  F05D2260/36 ,  Y02T50/676

    Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

    Abstract translation: 用于燃气涡轮发动机的冷却结构包括限定冷却腔的燃气涡轮发动机结构。 冷却部件构造成将冷却流沿所需方向引导到冷却腔中。 支架支撑冷却部件并且具有附接接口以将支架固定到燃气涡轮发动机结构。 与支架相关联的第一个定向功能。 第二定向特征与燃气涡轮发动机结构相关联。 第一和第二取向特征彼此配合以确保冷却部件仅相对于燃气涡轮发动机结构安装在一个方位上。 还公开了一种燃气涡轮发动机和安装冷却结构的方法。

    Retaining tab for diffuser seal ring
    5.
    发明授权
    Retaining tab for diffuser seal ring 有权

    公开(公告)号：US10808612B2

    公开(公告)日：2020-10-20

    申请号：US15165245

    申请日：2016-05-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： John D. Wiedemer ,  Dale William Petty ,  Jonathan Lemoine ,  Jason Arnold

    IPC: F01D25/24 ,  F02C7/04 ,  F01D11/02 ,  F01D11/00 ,  F01D11/12 ,  F16J15/44

    Abstract: An example diffuser assembly includes a diffuser case, an annular ring, and a retaining tab that is mounted to the annular ring and has an end that engages an inner wall of the diffuser case. The engagement between the second end and the inner wall locks the retaining tab and limits movement of the annular ring along a central longitudinal axis of the diffuser case. Another example diffuser assembly includes a diffuser case, an annular ring, and a snap ring. The snap ring is situated in an annular groove of an inner wall of the diffuser case, and restricts movement of the annular ring along a central longitudinal axis of the diffuser case. A retaining tab is affixed to either the annular ring or the diffuser case, and has an end retaining the annular ring in the annular groove.

    Compliant seal assembly and method of operating
    6.
    发明授权
    Compliant seal assembly and method of operating 有权

    公开(公告)号：US10047623B2

    公开(公告)日：2018-08-14

    申请号：US14938447

    申请日：2015-11-11

    Applicant: United Technologies Corporation

    Inventor： Jonathan Lemoine ,  Steven D. Porter

    IPC: F01D11/00 ,  F16J15/44 ,  F16J15/16 ,  F16J15/56 ,  F16J9/12 ,  F02C7/28 ,  F01D9/06 ,  F01D25/16

    Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.

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