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    Self-cooled orifice structure
    2.
    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.

    GAS TURBINE ENGINE COMPONENTS AND COOLING CAVITIES
    4.
    发明申请
    GAS TURBINE ENGINE COMPONENTS AND COOLING CAVITIES 审中-公开
    气体涡轮发动机组件和冷却空调

    公开(公告)号：US20160178201A1

    公开(公告)日：2016-06-23

    申请号：US14978044

    申请日：2015-12-22

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/26 ,  F23R3/286 ,  F23R2900/03043 ,  F23R2900/03045

    Abstract: The present disclosure relates to gas turbine engine components including cooling cavities. One embodiment is directed to a component including a forward surface, an aft surface, at least one inlet on the forward surface and a cavity between the forward surface and the aft surface. The cavity is configured to receive airflow from at least one inlet to provide cooling flow for the component. The cavity includes a plurality of structures within the cavity. The component also includes at least one exit between the forward surface and the aft surface. The plurality of structures are configured to meter air flow within the cavity and to maintain the cooling effectiveness of air flow within the cavity from the at least one inlet to the at least one exit. The component having a cavity may be employed by a combustor of a gas turbine engine.

    Abstract translation: 本公开涉及包括冷却腔的燃气涡轮发动机部件。 一个实施例涉及包括前表面，后表面，前表面上的至少一个入口和前表面和后表面之间的空腔的部件。 空腔构造成从至少一个入口接收气流以为部件提供冷却流。 空腔包括空腔内的多个结构。 该部件还包括在前表面和后表面之间的至少一个出口。 多个结构被配置为测量空腔内的空气流动并且保持空腔内的空气流从至少一个入口到至少一个出口的冷却效果。 具有空腔的部件可以由燃气涡轮发动机的燃烧器使用。

    Fuel injector guide(s) for a turbine engine combustor
    6.
    发明授权
    Fuel injector guide(s) for a turbine engine combustor 审中-公开

    公开(公告)号：US10670272B2

    公开(公告)日：2020-06-02

    申请号：US14939667

    申请日：2015-11-12

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka

    IPC: F23R3/28 ,  F23R3/10

    Abstract: A fuel injector guide is provided for a turbine engine combustor. The fuel injector guide includes a tubular base, an annular flange, a plurality of ribs and a flow turbulator. The base extends along an axis between first and second ends. The flange extends radially out from the base at the second end. The ribs are disposed around the base and extend axially out from the flange towards the first end. The flow turbulator is disposed between an adjacent pair of the ribs.

    NOZZLE GUIDE FOR A COMBUSTOR OF A GAS TURBINE ENGINE
    10.
    发明申请
    NOZZLE GUIDE FOR A COMBUSTOR OF A GAS TURBINE ENGINE 审中-公开
    燃气轮机发动机喷嘴指南

    公开(公告)号：US20160146465A1

    公开(公告)日：2016-05-26

    申请号：US14950876

    申请日：2015-11-24

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka

    IPC: F23R3/10 ,  F23R3/00

    CPC classification number: F23R3/002 ,  F23R3/283 ,  F23R2900/03043 ,  F23R2900/03044

    Abstract: A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.

    Abstract translation: 为燃气轮机的燃烧器提供喷嘴引导件。 所述喷嘴引导件包括环形结构，所述环形结构包括多个冷却孔，在所述导向板的外周上包括多个开口的引导板，以及在所述环形结构内的多个冷却通道，以提供来自所述多个冷却 孔到多个开口。

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