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    ASSEMBLY FOR SEALING A GAP BETWEEN COMPONENTS OF A TURBINE ENGINE
    12.
    发明申请
    ASSEMBLY FOR SEALING A GAP BETWEEN COMPONENTS OF A TURBINE ENGINE 审中-公开
    组装用于密封涡轮发动机部件之间的差距

    公开(公告)号：US20160017738A1

    公开(公告)日：2016-01-21

    申请号：US14770678

    申请日：2014-02-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark J. Rogers ,  Timothy M. Davis ,  Mark Broomer ,  Kevin W. White ,  Craig McGarrah ,  Carson A. Roy Thill

    IPC: F01D11/00 ,  F01D25/26

    CPC classification number: F01D11/005 ,  F01D25/26 ,  F02C7/28 ,  F05D2220/30 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2260/97 ,  F16J15/061 ,  F16J15/0812

    Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.

    Abstract translation: 涡轮发动机的组件包括涡轮发动机第一部件，涡轮发动机第二部件和密封组件。 第一部件包括凹槽和凹槽表面。 第二部件包括延伸到凹槽中的舌部到舌部表面。 密封组件至少部分地密封槽表面和舌表面之间的间隙。 密封组件包括绳索密封件和将绳索密封件附接到舌头的夹子。 绳密封件布置在槽表面和舌表面之间的槽内。

    SEAL ASSEMBLY WITH DISTRIBUTED COOLING ARRANGEMENT
    14.
    发明申请
    SEAL ASSEMBLY WITH DISTRIBUTED COOLING ARRANGEMENT 有权

    公开(公告)号：US20210254503A1

    公开(公告)日：2021-08-19

    申请号：US16819519

    申请日：2020-03-16

    Applicant: United Technologies Corporation

    Inventor： Carson A. Roy Thill ,  Justin K. Bleil ,  Andrew D. Keene ,  Jaime A. Arbona ,  Danielle Mahoney

    IPC: F01D25/12 ,  F01D11/08 ,  F01D5/20 ,  F01D5/18

    Abstract: An 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 pair of opposed rails extending outwardly from the sealing portion. The sealing portion includes a sealing face dimensioned to bound a core flow path and has a backside face opposed to the sealing face. The backside face includes a first localized region, a second localized region between the pair of rails, and a third localized region. A support includes a mounting portion and a first interface portion. At least one retention pin is dimensioned to engage the first interface portion of the support and at least one of the pair of rails such that the seal arc segment is carried by the at least one retention pin. A support plate is arranged relative to the support such that the at least one retention pin is trapped between the support plate and the support. A cooling cavity is established between the support, the support plate, and the second localized region. A method of sealing is also disclosed.

    CMC heat shield
    15.
    发明授权
    CMC heat shield 有权

    公开(公告)号：US11041399B2

    公开(公告)日：2021-06-22

    申请号：US16671288

    申请日：2019-11-01

    Applicant: United Technologies Corporation

    Inventor： Paul M. Lutjen ,  Carson A. Roy Thill

    IPC: F01D5/14 ,  F01D11/08

    Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and mounted in a carrier. At least two of the plurality of segments have a first wall that extends radially outward from a base portion. The base portion has a radially inner side and a radially outer side. A heat shield abuts the radially outer side of the at least two segments. The heat shield is formed from a ceramic material.

    ATTACHMENT ARRANGEMENT FOR TURBINE ENGINE COMPONENT
    18.
    发明申请
    ATTACHMENT ARRANGEMENT FOR TURBINE ENGINE COMPONENT 有权
    涡轮发动机组件的附件安装

    公开(公告)号：US20160362992A1

    公开(公告)日：2016-12-15

    申请号：US14736333

    申请日：2015-06-11

    Applicant: United Technologies Corporation

    Inventor： Carson A. Roy Thill ,  Russell E. Keene ,  Paul M. Lutjen

    IPC: F01D9/02 ,  F01D11/00 ,  F01D5/14

    CPC classification number: F01D9/02 ,  F01D5/14 ,  F01D9/04 ,  F01D11/003 ,  F01D11/005 ,  F01D25/246

    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.

    Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的部件尤其包括在前表面和后表面之间具有周向侧的主体，每个周向侧限定配合面，附接构件从 主体和与本体和附接构件相邻的过渡构件。 过渡构件和主体限定了构造成接收密封构件的槽。 过渡构件从周向侧之一向内倾斜。 还公开了一种制造燃气涡轮发动机部件的方法。

    Compact pin attachment for CMC components
    19.
    发明授权
    Compact pin attachment for CMC components 有权

    公开(公告)号：US11215064B2

    公开(公告)日：2022-01-04

    申请号：US16817990

    申请日：2020-03-13

    Applicant: United Technologies Corporation

    Inventor： Jaime A. Arbona ,  Carson A. Roy Thill ,  Justin K. Bleil

    IPC: F01D11/08 ,  F16B19/00

    Abstract: A component assembly includes a first component that has a first hole. The first hole has a non-circular cross section. A first portion of the first hole has a first radius of curvature and a second component. A pin extends from the second component and through the first hole. The pin has a non-circular cross section. A second portion of the pin has a second radius of curvature. The first radius of curvature and the second radius of curvature are substantially the same.

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