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    TRANSLATING COMPRESSOR AND TURBINE ROTORS FOR CLEARANCE CONTROL
    1.
    发明申请
    TRANSLATING COMPRESSOR AND TURBINE ROTORS FOR CLEARANCE CONTROL 审中-公开
    翻转压缩机和涡轮转子用于间隙控制

    公开(公告)号：WO2015065597A3

    公开(公告)日：2015-08-13

    申请号：PCT/US2014055336

    申请日：2014-09-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SMITH DARREN M

    IPC: F01D11/22

    CPC classification number: F01D11/22 ,  F01D17/02 ,  F01D17/20 ,  F02C7/36

    Abstract: A first actuator moves a compressor rotor and compressor blades along a rotational axis of the compressor rotor. A turbine rotor includes a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip. A turbine housing surrounds each of the turbine blade tips. The turbine housing has an inner surface, and a turbine tip clearance is defined between each of the turbine blade tips and the inner surface of the turbine housing. A second actuator moves the turbine rotor and the turbine blades along a rotational axis of the turbine rotor. A control controls the first actuator of the compressor rotor, and the second actuator of the turbine rotor to control the compressor tip clearance and the turbine tip clearance.

    Abstract translation: 第一致动器沿着压缩机转子的旋转轴线移动压缩机转子和压缩机叶片。 涡轮转子包括多个涡轮机叶片，每个涡轮叶片从涡轮机转子径向向外延伸到外部末端。 涡轮机壳体围绕每个涡轮机叶片尖端。 涡轮壳体具有内表面，并且涡轮机顶端间隙限定在涡轮机叶片尖端和涡轮机壳体的内表面之间。 第二致动器沿着涡轮机转子的旋转轴线移动涡轮转子和涡轮机叶片。 控制器控制压缩机转子的第一致动器和涡轮转子的第二致动器以控制压缩机顶端间隙和涡轮机顶端间隙。

    ROUNDED EDGES FOR GAS PATH COMPONENTS
    2.
    发明申请
    ROUNDED EDGES FOR GAS PATH COMPONENTS 审中-公开
    用于气体路径组件的圆形边缘

    公开(公告)号：WO2015050603A3

    公开(公告)日：2015-06-25

    申请号：PCT/US2014044232

    申请日：2014-06-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SMITH DARREN M

    IPC: F02C7/00 ,  F02C7/20

    CPC classification number: F23R3/002 ,  F01D9/023 ,  F01D25/24 ,  F02C7/24 ,  F02K1/82 ,  F02K1/822 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2300/611 ,  Y02T50/675

    Abstract: A gas turbine engine section has a housing and a plurality of panels attached to the housing. The panels face toward a flow path of hot products of combustion. The panels include a central web and extending legs. A bend between the central web and the extending legs is formed at a radius. A gas turbine engine is also disclosed.

    Abstract translation: 燃气涡轮发动机部分具有壳体和附接到壳体的多个面板。 面板面向热燃烧产物的流路。 面板包括中央腹板和延伸腿。 在中心腹板和延伸腿之间的弯曲形成为半径。 还公开了一种燃气涡轮发动机。

    TRANSLATING COMPRESSOR AND TURBINE ROTORS FOR CLEARANCE CONTROL
    4.
    发明公开
    TRANSLATING COMPRESSOR AND TURBINE ROTORS FOR CLEARANCE CONTROL 有权
    ÜBERSETZUNGSVERDICHTERTURBINENROTOREN ZUR ABSTANDSSTEUERUNG

    公开(公告)号：EP3052769A4

    公开(公告)日：2016-11-09

    申请号：EP14856933

    申请日：2014-09-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SMITH DARREN M

    IPC: F01D11/22 ,  F01D17/02 ,  F01D17/20 ,  F02C7/36

    CPC classification number: F01D11/22 ,  F01D17/02 ,  F01D17/20 ,  F02C7/36

    Abstract: A first actuator moves a compressor rotor and compressor blades along a rotational axis of the compressor rotor. A turbine rotor includes a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip. A turbine housing surrounds each of the turbine blade tips. The turbine housing has an inner surface, and a turbine tip clearance is defined between each of the turbine blade tips and the inner surface of the turbine housing. A second actuator moves the turbine rotor and the turbine blades along a rotational axis of the turbine rotor. A control controls the first actuator of the compressor rotor, and the second actuator of the turbine rotor to control the compressor tip clearance and the turbine tip clearance.

    Abstract translation: 第一致动器沿着压缩机转子的旋转轴线移动压缩机转子和压缩机叶片。 涡轮转子包括多个涡轮机叶片，每个涡轮叶片从涡轮机转子径向向外延伸到外部末端。 涡轮机壳体围绕每个涡轮机叶片尖端。 涡轮机壳体具有内表面，并且涡轮机顶端间隙被限定在每个涡轮机叶片尖端和涡轮机壳体的内表面之间。 第二致动器沿着涡轮机转子的旋转轴线移动涡轮转子和涡轮机叶片。 控制器控制压缩机转子的第一致动器和涡轮转子的第二致动器以控制压缩机顶端间隙和涡轮机顶端间隙。

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