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    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION
    3.
    发明申请
    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION 审中-公开

    公开(公告)号：WO2013141949A3

    公开(公告)日：2013-09-26

    申请号：PCT/US2013/020973

    申请日：2013-01-10

    Applicant: UNITED TECHNOLOGIES CORPORATION ,  GAUTSCHI, Steven Bruce ,  SPANGLER, Brandon W. ,  QUACH, San ,  MONGILLO, Dominic J. Jr.

    Inventor： GAUTSCHI, Steven Bruce ,  SPANGLER, Brandon W. ,  QUACH, San ,  MONGILLO, Dominic J. Jr.

    IPC: F01D5/08

    Abstract: An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The trailing edge region is located axially downstream from the leading edge and terminates in a trailing edge. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators are located in the cooling passageway adjacent the trailing edge. The column of flow separators includes a first flow separator having a first longitudinal axis offset to a second flow separator having a second longitudinal axis.

    LOST CORE MOLDING CORES FOR FORMING COOLING PASSAGES
    4.
    发明申请
    LOST CORE MOLDING CORES FOR FORMING COOLING PASSAGES 审中-公开
    用于形成冷却通道的失蜡芯线

    公开(公告)号：WO2015060989A1

    公开(公告)日：2015-04-30

    申请号：PCT/US2014/057574

    申请日：2014-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： THORNTON, Lane ,  QUACH, San ,  GAUTSCHI, Steven Bruce

    IPC: B22C9/04 ,  B22C7/02

    CPC classification number: B22C9/103 ,  B22C9/24

    Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.

    Abstract translation: 在特征实施例中，失去的芯组件包括在径向上具有锥形形状的陶瓷部件。 难熔金属部件从陶瓷芯部件径向延伸。 还公开了一种模制燃气涡轮发动机部件的方法。

    GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT
    5.
    发明申请
    GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT 审中-公开
    气体涡轮发动机组件冷却电路

    公开(公告)号：WO2014047022A1

    公开(公告)日：2014-03-27

    申请号：PCT/US2013/060039

    申请日：2013-09-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GAUTSCHI, Steven Bruce ,  THORNTON, Lane

    IPC: F02C7/12 ,  F01D5/08

    CPC classification number: F01D5/189 ,  F05D2240/126 ,  Y02T50/676

    Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling circuit disposed inside of the body portion. The cooling circuit includes a first baffle received within a first core cavity that extends inside of the body portion, a second baffle received within a second core cavity that extends inside of the body portion, and a first rib disposed between the first core cavity and the second core cavity. The first baffle is in fluid communication with the second baffle through the first rib.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括设置在主体部分内部的主体部分和冷却回路。 冷却回路包括容纳在主体部分内部延伸的第一芯腔内的第一挡板，容纳在主体部分内延伸的第二芯腔内的第二挡板以及设置在第一芯腔和第二芯腔之间的第一肋 第二核心腔。 第一挡板通过第一肋与第二挡板流体连通。

    FAN COOLING HOLE ARRAY
    7.
    发明申请
    FAN COOLING HOLE ARRAY 审中-公开
    风扇冷却孔阵列

    公开(公告)号：WO2015163949A3

    公开(公告)日：2015-10-29

    申请号：PCT/US2015/010010

    申请日：2015-01-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： THORNTON, Lane ,  DEVORE, Matthew A. ,  MONGILLO, Dominic J. ,  GAUTSCHI, Steven Bruce

    IPC: F01D5/18

    Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.

    Abstract translation: 燃气涡轮发动机部件包括翼型，翼型具有从前缘延伸到后缘的吸入侧和压力侧。 在前缘附近有多个冷却孔，冷却孔具有非圆形形状，具有较长的尺寸和较小的尺寸。 翼型限定从径向外端到径向内端的径向方向，并且径向外部的朝向径向外端间隔开的冷却孔具有更接近平行于径向方向延伸的较长尺寸。 与径向外部冷却孔相比，更靠近具有较长尺寸的径向内端的径向内部冷却孔延伸至相对于径向方向更接近垂直。

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