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    Blade outer air seal assembly with positioning feature for gas turbine engine
    21.
    发明授权
    Blade outer air seal assembly with positioning feature for gas turbine engine 有权

    公开(公告)号：US10280799B2

    公开(公告)日：2019-05-07

    申请号：US15178896

    申请日：2016-06-10

    Applicant: United Technologies Corporation

    Inventor： Timothy M. Davis

    IPC: F01D25/24 ,  F01D5/02 ,  F01D5/12 ,  F01D11/08

    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment that has a sealing portion and a first interface portion. The first interface portion defines circumferential mate faces. A support includes a mounting portion and a second interface portion. The mounting portion is configured to be fixedly attached to an engine static structure, and the second interface portion is radially inward of the first interface portion. At least one positioning member is dimensioned to abut the first and second interface portions such that the first and second interface portions are spaced apart by a predetermined distance in a radial direction.

    BRUSH SEAL WITH EXTENDED BACKING PLATE
    22.
    发明申请
    BRUSH SEAL WITH EXTENDED BACKING PLATE 审中-公开

    公开(公告)号：US20190063248A1

    公开(公告)日：2019-02-28

    申请号：US15687900

    申请日：2017-08-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark J. Rogers ,  Timothy M. Davis

    IPC: F01D11/00

    CPC classification number: F01D11/006 ,  F01D11/005 ,  F05D2240/56 ,  F16J15/3288

    Abstract: A seal system may comprise a seal cavity defined, at least partially, by a first axial surface and a second axial surface. The second axial surface may be recessed with respect to the first axial surface. A brush seal may be disposed in the seal cavity. The brush seal may comprise a first bristle pack and a backing plate coupled to the first bristle pack. A first group of bristles of the first bristle pack may be radially inward of the first axial surface.

    Thermally protected seal assembly
    25.
    发明授权
    Thermally protected seal assembly 有权

    公开(公告)号：US10088049B2

    公开(公告)日：2018-10-02

    申请号：US14704634

    申请日：2015-05-05

    Applicant: United Technologies Corporation

    Inventor： Timothy M. Davis ,  Michael S. Stevens

    IPC: F16J15/08 ,  F01D11/00

    Abstract: A seal assembly that may be for turbine engine includes first and second rings with a convoluted seal resiliently compressed there-between. The seal may define a gap for receipt of a thermally resistant shield that may also reduce wear of the seal. The seal may include a hole for the flow of cooling air and the shield may be porous so as not to obstruct the cooling air flow for cooling of the seal.

    TURBINE ENGINE TIP CLEARANCE CONTROL SYSTEM WITH ROCKER ARMS
    28.
    发明申请
    TURBINE ENGINE TIP CLEARANCE CONTROL SYSTEM WITH ROCKER ARMS 有权
    涡轮发动机提升间隙控制系统

    公开(公告)号：US20160356169A1

    公开(公告)日：2016-12-08

    申请号：US14731140

    申请日：2015-06-04

    Applicant: United Technologies Corporation

    Inventor： Brian Duguay ,  Timothy M. Davis

    IPC: F01D11/22

    CPC classification number: F01D11/22 ,  F01D11/14 ,  F01D11/20

    Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes a blade outer air seal segment, a linkage, a rocker arm and an actuation device. The linkage is attached to the blade outer air seal segment. The rocker arm includes a first arm and a second arm engaged with the linkage. The actuation device is engaged with the first arm. The actuation device is configured to pivot the rocker arm and thereby radially move the blade outer air seal segment.

    Abstract translation: 为具有轴向中心线的涡轮发动机提供组件。 该涡轮发动机组件包括叶片外部空气密封段，连杆机构，摇臂和致动装置。 连接件连接到叶片外部空气密封段。 摇臂包括与连杆相配合的第一臂和第二臂。 致动装置与第一臂接合。 致动装置构造成枢转摇臂，从而径向移动叶片外部空气密封段。

    SPLINED HONEYCOMB SEALS
    29.
    发明申请
    SPLINED HONEYCOMB SEALS 审中-公开
    螺旋蜂窝密封

    公开(公告)号：US20160208926A1

    公开(公告)日：2016-07-21

    申请号：US15022838

    申请日：2014-07-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Timothy M. Davis ,  Jeffrey Vincent Anastas

    IPC: F16J15/34 ,  F01D11/00

    CPC classification number: F16J15/3496 ,  F01D9/02 ,  F01D11/001 ,  F01D11/003 ,  F01D11/08 ,  F01D11/12 ,  F01D11/122 ,  F01D11/125 ,  F01D11/127 ,  F01D11/22 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/283 ,  F16J15/3464 ,  F16J15/444

    Abstract: A seal assembly includes an annular carrier defining a radially inward face, and an opposed radially outward face defining a plurality of spline slots. The spline slots are configured and adapted to receive corresponding spline tabs to center the carrier in a surrounding structure. A honeycomb seal is mounted to the radially inward face of the carrier. The honeycomb seal is configured for sealing engagement with a knife-edge seal rotating relative to the honeycomb seal. The seal assembly has a relatively low coefficient of thermal expansion in comparison to the static component or the knife-edge seal. For example, a gas turbine engine can include a seal assembly as described above, wherein the carrier is mounted to a static component and a rotor mounted for rotation relative to the carrier, and wherein the rotor includes the knife edge seal component sealingly engaged to the honeycomb seal.

    Abstract translation: 密封组件包括限定径向内表面的环形载体和限定多个花键槽的相对的径向向外的面。 花键槽被配置并适于接收相应的花键突片，以使载体在周围的结构中居中。 蜂窝密封件安装在载体的径向向内的表面上。 蜂窝状密封件构造成与相对于蜂窝密封件旋转的刀刃密封件密封接合。 与静态部件或刀刃密封件相比，密封组件具有相对低的热膨胀系数。 例如，燃气涡轮发动机可以包括如上所述的密封组件，其中载体被安装到静止部件和安装成相对于载体旋转的转子，并且其中转子包括密封地接合到 蜂窝密封。

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