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    Rim seal for gas turbine engine
    12.
    发明授权
    Rim seal for gas turbine engine 有权

    公开(公告)号：US10533445B2

    公开(公告)日：2020-01-14

    申请号：US15244203

    申请日：2016-08-23

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Christopher Corcoran ,  Bryan P. Dube

    IPC: F01D11/00 ,  F01D5/02 ,  F01D5/30 ,  F02C3/04 ,  F04D29/08 ,  F04D29/32

    Abstract: A rim seal for a rotor of a gas turbine engine includes a seal portion extending circumferentially across a rim cavity of a rotor, the sealing portion configured to seal the rim cavity and a first foot portion extending radially inwardly from a first end of the sealing portion. A rotor assembly for a gas turbine engine includes a rotor disc and a plurality of rotor blades secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the sealing portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end of the rim seal and from a second end opposite the first end.

    MODULATED COMBUSTOR BYPASS AND COMBUSTOR BYPASS VALVE
    13.
    发明申请
    MODULATED COMBUSTOR BYPASS AND COMBUSTOR BYPASS VALVE 审中-公开

    公开(公告)号：US20190211751A1

    公开(公告)日：2019-07-11

    申请号：US15864266

    申请日：2018-01-08

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Stephen K. Kramer

    IPC: F02C9/18 ,  F23R3/26 ,  F02C9/22

    CPC classification number: F02C9/18 ,  F01D17/145 ,  F01D17/162 ,  F05D2240/35 ,  F23R3/26

    Abstract: A combustor section of a gas turbine engine includes a combustor having a combustor inlet, and a combustor bypass passage having a passage inlet located upstream of the combustor inlet, the combustor bypass passage configured to divert a selected bypass airflow around the combustor. A combustor bypass valve is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. The combustor bypass valve including a valve element configured to rotate about an engine central longitudinal axis A to move one or more valve openings relative to one or more bypass passage openings.

    GAS TURBINE ENGINE VANE-TO-TRANSITION DUCT SEAL
    15.
    发明申请
    GAS TURBINE ENGINE VANE-TO-TRANSITION DUCT SEAL 审中-公开
    气体涡轮发动机转向转向密封

    公开(公告)号：US20140366556A1

    公开(公告)日：2014-12-18

    申请号：US14296657

    申请日：2014-06-05

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Robert L. Hazzard

    IPC: F01D11/00

    CPC classification number: F01D11/005 ,  F01D25/246

    Abstract: A vane seal assembly for a gas turbine engine comprises of a case including a first connector. A notch in the case adjoins the groove. A vane having a second connector mates with the first connector. A seal assembly is provided between the vane and the case to provide a sealed cavity adjoining the notch.

    Abstract translation: 一种用于燃气涡轮发动机的叶片密封组件，包括一个包括第一连接器的壳体。 这种情况下的凹口与凹槽相邻。 具有第二连接器的叶片与第一连接器配合。 密封组件设置在叶片和壳体之间以提供与凹口相邻的密封腔。

    Modulated combustor bypass and combustor bypass valve
    16.
    发明授权
    Modulated combustor bypass and combustor bypass valve 有权

    公开(公告)号：US11060463B2

    公开(公告)日：2021-07-13

    申请号：US15864266

    申请日：2018-01-08

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Stephen K. Kramer

    IPC: F02C9/18 ,  F02C9/22 ,  F23R3/26 ,  F02C9/54 ,  F02C6/08

    Abstract: A combustor section of a gas turbine engine includes a combustor having a combustor inlet, and a combustor bypass passage having a passage inlet located upstream of the combustor inlet, the combustor bypass passage configured to divert a selected bypass airflow around the combustor. A combustor bypass valve is located at the combustor bypass passage to control the selected bypass airflow along the combustor bypass passage. The combustor bypass valve including a valve element configured to rotate about an engine central longitudinal axis A to move one or more valve openings relative to one or more bypass passage openings.

    Ceramic core setter
    17.
    发明授权
    Ceramic core setter 有权

    公开(公告)号：US11014140B2

    公开(公告)日：2021-05-25

    申请号：US16384664

    申请日：2019-04-15

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Lea Dynnette Castle

    IPC: B22C9/10 ,  B21D37/10 ,  B21D37/14 ,  B22C21/14

    Abstract: A die setting apparatus for a ceramic core is provided. The die setting apparatus includes a first setter abuttable with a first side of the ceramic core and a second setter abuttable with a second side of the ceramic core opposite the first side. At least one of the first and second setters includes two or more pieces respectively arranged to form one or more gaps. Each of the one or more gaps is oriented to thermally adjust in correspondence with thermal changes of the ceramic core during a firing process thereof.

    Turbine blade tip wall cooling
    18.
    发明授权
    Turbine blade tip wall cooling 有权

    公开(公告)号：US11008873B2

    公开(公告)日：2021-05-18

    申请号：US16267664

    申请日：2019-02-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Anton G. Banks ,  Lane Mikal Thornton

    IPC: F01D5/18

    Abstract: A gas turbine engine blade according to an example of the present disclosure includes a blade including internal walls defining a blade cooling passage and a tip section at a radially outer end of the blade. The tip section includes a pocket protruding into the tip section from a radially outermost end of the tip section to a pocket floor. The blade further includes a pocket wall defined between the pocket floor and the radially outermost end of the tip section and including a tapered wall cooling passage.

    CERAMIC CORE SETTER
    19.
    发明申请
    CERAMIC CORE SETTER 审中-公开

    公开(公告)号：US20200324333A1

    公开(公告)日：2020-10-15

    申请号：US16384664

    申请日：2019-04-15

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Lea Dynnette Castle

    IPC: B21D37/10 ,  B22C9/10 ,  B21D37/14

    Abstract: A die setting apparatus is provided for a ceramic core is provided. The die setting apparatus includes a first setter abuttable with a first side of the ceramic core and a second setter abuttable with a second side of the ceramic core opposite the first side. At least one of the first and second setters includes two or more pieces respectively arranged to form one or more gaps. Each of the one or more gaps is oriented to thermally adjust in correspondence with thermal changes of the ceramic core during a firing process thereof.

    AIRFOIL WITH TRAILING EDGE ROUNDING
    20.
    发明申请
    AIRFOIL WITH TRAILING EDGE ROUNDING 审中-公开

    公开(公告)号：US20200032657A1

    公开(公告)日：2020-01-30

    申请号：US16043257

    申请日：2018-07-24

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Alan C. Barron

    IPC: F01D5/18 ,  F01D5/28 ,  F01D5/14

    Abstract: An airfoil for a gas turbine engine includes a substrate portion extending from an airfoil leading edge to an airfoil trailing edge portion. The airfoil trailing edge portion includes a flared portion wherein a substrate portion thickness increases along a camber line of the airfoil, and a trailing edge defined as a full constant radius extending from a pressure side of the airfoil to a suction side of the airfoil. A coating portion includes a coating applied over at least a portion of the substrate portion.

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