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    TURBINE AIRFOIL COOLING CORE EXIT
    12.
    发明公开
    TURBINE AIRFOIL COOLING CORE EXIT 审中-公开
    汽轮机冷却启动器

    公开(公告)号：EP3060761A4

    公开(公告)日：2016-10-19

    申请号：EP14856429

    申请日：2014-09-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： QUACH SAN ,  SLAVENS THOMAS N

    IPC: F01D5/18 ,  B22C9/10 ,  F01D25/12 ,  F02C7/18

    CPC classification number: F01D5/187 ,  B22C9/00 ,  B22C9/10 ,  B22C9/24 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/31 ,  F05D2230/50 ,  F05D2240/305 ,  F05D2240/307 ,  F05D2260/20 ,  Y02T50/676

    Abstract: A gas turbine engine component has an airfoil extending from a platform to a tip at an end of the airfoil spaced from the platform. The airfoil has a suction wall and a pressure wall, with at least one channel extending toward the tip from the platform. A plenum communicates with the at least one channel. The plenum flows from the suction wall toward the pressure wall at the tip to communicate with cooling holes near the pressure wall. The plenum has a reduced cross-sectional area between the suction wall and the pressure wall, and an increase in cross-sectional area downstream of the reduced cross-sectional area. A mold core is also disclosed.

    Abstract translation: 燃气涡轮发动机部件具有从平台延伸到在与平台间隔开的翼型的端部处的尖端的翼型件。 翼型件具有吸力壁和压力壁，至少一个通道从平台向尖端延伸。 一个通风室与至少一个通道通信。 气室从吸力壁流向尖端处的压力壁，以与压力壁附近的冷却孔连通。 增压室在吸力壁和压力壁之间具有减小的横截面积，并且在减小的横截面积的下游的横截面面积增加。 还公开了一种模芯。

    AIRFOIL COOLING CIRCUITS
    14.
    发明公开
    AIRFOIL COOLING CIRCUITS 审中-公开
    冷却回路翼

    公开(公告)号：EP2867476A4

    公开(公告)日：2015-08-12

    申请号：EP13822892

    申请日：2013-04-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUDSON ERIC A ,  PROPHETER-HINCKLEY TRACY A ,  QUACH SAN ,  DEVORE MATTHEW A

    IPC: F01D5/18 ,  F01D5/14 ,  F02C7/00

    CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/108 ,  B22C9/24 ,  F01D5/186 ,  F05D2230/211 ,  F05D2260/204 ,  F05D2260/2212

    Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

    LOST CORE STRUCTURAL FRAME
    15.
    发明公开
    LOST CORE STRUCTURAL FRAME 审中-公开
    STRUKTURRAHMEN MIT VERLORENEM KERN

    公开(公告)号：EP3086893A4

    公开(公告)日：2017-08-23

    申请号：EP14883263

    申请日：2014-11-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TAFFET STEVEN ,  DONNELL BRANDON S ,  NADEAU DANIEL C ,  DEIBEL RUSSELL ,  QUACH SAN

    IPC: B22C9/10 ,  B22C7/02 ,  B22C9/04 ,  B22C9/22 ,  B22C9/24 ,  F01D5/18 ,  F01D9/04

    CPC classification number: F01D5/187 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/323 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

    Abstract translation: 失芯模具部件包括第一腿部和第二腿部，第二腿部具有连接第一腿部和第二腿部的多个交叉部件。 多个交叉部件包括彼此间隔开的最外侧交叉部件。 第一支腿和第二支腿中的每一个的相邻末端以及第二交叉构件彼此间隔得比最外侧交叉构件更靠近彼此。 中央交叉部件在第一腿和第二腿之间以及第二交叉部件之间延伸。 最外面的跨接构件延伸第一横截面区域。 第二交叉部件延伸第二横截面区域，并且中央交叉部件延伸第三横截面区域。 第一横截面积大于第二横截面积。 第二横截面积大于第三横截面积。 燃气涡轮发动机和部件也被公开。

    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION
    16.
    发明公开
    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION 审中-公开
    HINTERKANTEN- ODER SPITZENFLAGGEN-FLUSSTRENNUNG

    公开(公告)号：EP2828485A4

    公开(公告)日：2016-07-27

    申请号：EP13763814

    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 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 is located in the cooling passageway adjacent the trailing edge and 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，冷却通道和流动分离器柱。 吸力表面和压力表面两者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，以限定翼型的中心空腔。 冷却通道位于后缘区域的中心腔内。 流动分离器的柱位于与后缘相邻的冷却通道中，并且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。

    LOST CORE MOLDING CORES FOR FORMING COOLING PASSAGES
    18.
    发明公开
    LOST CORE MOLDING CORES FOR FORMING COOLING PASSAGES 审中-公开
    FORMUNG VON KERNEN ZUR HERSTELLUNG VONKÜHLKANÄLEN

    公开(公告)号：EP3060363A4

    公开(公告)日：2017-07-26

    申请号：EP14856477

    申请日：2014-09-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THORNTON LANE ,  QUACH SAN ,  GAUTSCHI STEVEN BRUCE

    IPC: B22C9/04 ,  B22C7/02

    CPC classification number: B22C9/103

    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，迷路芯组件包括沿径向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。

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