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    Re-use and modulated cooling from tip clearance control system for gas turbine engine
    4.
    发明授权
    Re-use and modulated cooling from tip clearance control system for gas turbine engine 有权

    公开(公告)号：US10815814B2

    公开(公告)日：2020-10-27

    申请号：US15588911

    申请日：2017-05-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark F. Zelesky ,  Brian Merry ,  Gabriel L. Suciu

    IPC: F01D11/20 ,  F01D11/24 ,  F01D11/16 ,  F01D11/14

    Abstract: A control system for a gas turbine engine comprises a case structure, a clearance control ring mounted for movement relative to the case structure, an outer air seal mounted to the clearance control ring and facing a first engine component, and a control and valve assembly that receives flow from a flow input source. The control and valve assembly is configured to direct flow into a first cavity positioned radially between the case structure and the outer air seal, and wherein the control and valve assembly is configured to direct flow into a second cavity positioned downstream of the first cavity to interact with a second engine component. A method of controlling flow between a compressor section and turbine section is also disclosed.

    Gas turbine engine compressor rotor vaporization cooling
    5.
    发明授权
    Gas turbine engine compressor rotor vaporization cooling 有权

    公开(公告)号：US10364679B2

    公开(公告)日：2019-07-30

    申请号：US15102341

    申请日：2014-12-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark F. Zelesky ,  Michael Winter ,  Paul E. Coderre ,  Richard L. Sykes

    IPC: F01D5/08 ,  F02C7/16 ,  F02C3/04 ,  F01D5/18 ,  F01D5/34

    Abstract: A gas turbine engine rotor includes a rotor that provides a cooling cavity. The cooling cavity has a first chamber and a second chamber that are fluidly connected to one another by a passageway. At least one of the first and second rotor portions is configured to support a blade that is fluidly isolated from the cavity. A phase change material is arranged in the cavity. The phase change material is configured to be arranged in the first chamber in a first state and in the second chamber in the second state. The passageway is configured to carry the phase change material between the second and first chambers once changed between the first and second states.

    Self-cooled orifice structure
    10.
    发明授权
    Self-cooled orifice structure 有权

    公开(公告)号：US09851105B2

    公开(公告)日：2017-12-26

    申请号：US14790970

    申请日：2015-07-02

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Joel H. Wagner ,  Mark F. Zelesky ,  Stanislav Kostka ,  Timothy S. Snyder

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.

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