GAS TURBINE ENGINE COMPONENT WITH EMBEDDED DATA
    1.
    发明申请
    GAS TURBINE ENGINE COMPONENT WITH EMBEDDED DATA 审中-公开
    具有嵌入式数据的气体涡轮发动机部件

    公开(公告)号:US20150308337A1

    公开(公告)日:2015-10-29

    申请号:US14263679

    申请日:2014-04-28

    Abstract: A component for a gas turbine engine is disclosed. The component includes at least a first portion and a second portion, and a data representing matrix. The second portion includes a second portion surface. The data representing matrix is formed directly on the second portion surface and includes a plurality of contrasting cells arranged in a geometric pattern representing information about the component including test data, a serial number, and a part number. The plurality of contrasting cells includes a plurality of first cells and a plurality of second cells that contrast from the plurality of first cells.

    Abstract translation: 公开了一种用于燃气涡轮发动机的部件。 该组件至少包括第一部分和第二部分,以及表示矩阵的数据。 第二部分包括第二部分表面。 数据表示矩阵直接形成在第二部分表面上,并且包括以表示关于包括测试数据,序列号和部件号的部件的信息的几何图形布置的多个对比单元。 多个对比单元包括多个第一单元和与多个第一单元对比的多个第二单元。

    CRIMPED INSERT FOR IMPROVED TURBINE VANE INTERNAL COOLING
    2.
    发明申请
    CRIMPED INSERT FOR IMPROVED TURBINE VANE INTERNAL COOLING 有权
    用于改进涡轮风扇内部冷却的危险插件

    公开(公告)号:US20160201489A1

    公开(公告)日:2016-07-14

    申请号:US14593998

    申请日:2015-01-09

    CPC classification number: F01D9/047 F01D5/189 F01D9/02

    Abstract: An insert tube of a turbine vane is disclosed. The insert tube includes a pressure side wall, a suction side wall opposite and spaced apart from the pressure side wall, a leading edge, and a trailing edge opposite the leading edge. The insert tube includes a plurality of cooling channels spaced along the pressure side wall. The insert tube includes an indented portion located between the trailing edge and the pressure side wall.

    Abstract translation: 公开了一种涡轮叶片的插入管。 插入管包括压力侧壁,与压力侧壁相对且间隔开的吸力侧壁,前缘和与前缘相对的后缘。 插入管包括沿着压力侧壁间隔开的多个冷却通道。 插入管包括位于后缘和压力侧壁之间的凹入部分。

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