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    GAS TURBINE ENGINE AIRFOIL HAVING SERPENTINE FED PLATFORM COOLING PASSAGE
    11.
    发明申请
    GAS TURBINE ENGINE AIRFOIL HAVING SERPENTINE FED PLATFORM COOLING PASSAGE 审中-公开
    具有SERPENTINE FED平台冷却通气的气体涡轮发动机

    公开(公告)号：WO2015080783A2

    公开(公告)日：2015-06-04

    申请号：PCT/US2014055332

    申请日：2014-09-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GAYMAN SCOTT W ,  SPANGLER BRANDON W

    IPC: F01D5/18 ,  F02C7/18

    CPC classification number: F01D5/187 ,  F05D2240/81 ,  F05D2250/185

    Abstract: A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between the walls and has a first passageway that extends from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end. A platform cooling passageway is fluidly connected to the end and extends transversely into the platform. A cooling hole fluidly connects the platform cooling passageway to an exterior surface.

    Abstract translation: 燃气涡轮发动机翼型件包括平台和间隔开的壁，其提供从平台径向延伸到与平台相对的端部的外部翼面表面。 蛇形冷却通道布置在壁之间并且具有从平台朝向端部延伸的第一通道和流体连接到第一通道并从端部朝向平台延伸到端部的第二通道。 平台冷却通道流体地连接到端部并横向延伸到平台中。 冷却孔将平台冷却通道流畅地连接到外表面。

    GAS TURBINE ENGINE COMPONENT HAVING TRIP STRIPS
    12.
    发明申请
    GAS TURBINE ENGINE COMPONENT HAVING TRIP STRIPS 审中-公开
    具有牵引车的气体涡轮发动机部件

    公开(公告)号：WO2015023338A3

    公开(公告)日：2015-05-14

    申请号：PCT/US2014039350

    申请日：2014-05-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  MONGILLO DOMINIC J

    IPC: F02C7/18 ,  F01D5/18 ,  F01D25/12

    CPC classification number: F01D5/188 ,  F01D5/02 ,  F01D5/189 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.

    Abstract translation: 公开了一种燃气涡轮发动机，其包括压缩机部和涡轮部。 燃气涡轮发动机包括燃气涡轮发动机部件，其具有提供燃气涡轮发动机部件的外表面的第一壁和与第一壁间隔开的第二壁。 第一壁是暴露于燃气涡轮发动机的核心流动路径的气体通道壁。 第二个墙是非气道壁。 在第二壁和第一壁之间设置冷却通道。 第二壁具有设置在其上的跳闸条。

    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION
    14.
    发明申请
    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION 审中-公开
    跟踪边缘或提示标签防流动分离

    公开(公告)号：WO2013141949A2

    公开(公告)日：2013-09-26

    申请号：PCT/US2013020973

    申请日：2013-01-10

    Applicant: UNITED TECHNOLOGIES CORP ,  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: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2240/122 ,  F05D2240/125 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/314 ,  F05D2250/324 ,  F05D2260/22141 ,  Y02T50/676

    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 and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.

    Abstract translation: 翼型件包括前缘，后缘区域，吸力表面，压力表面，冷却通道和流动隔板柱。 后缘区域位于前缘的轴向下游并终止于后缘。 吸力表面和压力表面都在前缘和后缘区域之间轴向延伸，并且从翼型的根部径向延伸到翼型的尖端部分，以限定翼型的中心腔。 冷却通道位于后缘区域的中心腔内。 流分离器柱位于靠近后缘的冷却通道中。 流分离器的柱包括具有第一纵向轴线的第一流动分离器和具有第二纵向轴线的第二流动分离器。 第一纵向轴线相对于第一纵向轴线以一定角度偏移。

    GAS TURBINE ENGINE COMPONENT HAVING SUCTION SIDE CUTBACK OPENING
    20.
    发明公开
    GAS TURBINE ENGINE COMPONENT HAVING SUCTION SIDE CUTBACK OPENING 审中-公开
    GASTURBINENMOTORKOMPONENTE MITRÜCKSCHLAGSÖFFNUNGAUF DER ABSAUGSEITE

    公开(公告)号：EP2938858A4

    公开(公告)日：2016-11-02

    申请号：EP13869160

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W

    IPC: F02C7/12 ,  F01D5/18

    CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2240/304 ,  F05D2250/52

    Abstract: An airfoil for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a pressure side wall and a suction side wall spaced apart from the pressure side wall and each extending between a leading edge portion and a trailing edge portion. A plurality of cutback openings are spaced along a radial axis of the suction side wall.

    Abstract translation: 根据本公开的示例性方面，用于燃气涡轮发动机的翼型件包括压力侧壁和与压力侧壁间隔开的每个在前缘部分和尾部之间延伸的吸力侧壁 边缘部分。 多个切口开口沿着吸力侧壁的径向轴线间隔开。

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