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    AIRFOIL COOLING CIRCUITS
    3.
    发明申请
    AIRFOIL COOLING CIRCUITS 审中-公开
    空气冷却电路

    公开(公告)号：WO2014018138A2

    公开(公告)日：2014-01-30

    申请号：PCT/US2013037302

    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.

    Abstract translation: 机翼包括前缘和后缘; 第一和第二侧从前缘延伸到后缘，每个侧面具有外表面; 位于第一和第二侧之间以及前缘和后缘之间的芯通道; 以及位于所述芯通道和所述第一侧的外表面之间的壁结构。 所述壁结构包括与所述芯通道连通的多个冷却流体入口，用于从所述芯通道接收冷却流体;在所述第一侧的外表面上的多个冷却流体出口，用于排出冷却流体，并沿着所述外部形成冷却膜 第一侧的表面，以及与多个冷却流体入口和多个冷却流体出口连通的多个冷却通道。 一个冷却通道的至少一部分在相邻的冷却流体出口之间延伸。

    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION
    4.
    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。

    LOST CORE STRUCTURAL FRAME
    5.
    发明申请
    LOST CORE STRUCTURAL FRAME 审中-公开
    失去核心结构框架

    公开(公告)号：WO2015126488A3

    公开(公告)日：2015-11-05

    申请号：PCT/US2014066495

    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 ,  B22C9/22 ,  F01D5/18

    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。

    SHARK-BITE TIP SHELF COOLING CONFIGURATION
    6.
    发明申请
    SHARK-BITE TIP SHELF COOLING CONFIGURATION 审中-公开
    SHARK-BITE TIP SHELF冷却配置

    公开(公告)号：WO2013180797A3

    公开(公告)日：2014-01-23

    申请号：PCT/US2013030706

    申请日：2013-03-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： QUACH SAN

    IPC: F01D5/30 ,  F01D11/00 ,  F02C7/14 ,  F02K3/00

    CPC classification number: F01D5/187 ,  F01D5/20 ,  F05D2240/305 ,  F05D2240/307 ,  F05D2250/11 ,  F05D2250/183 ,  F05D2260/202 ,  Y02T50/676

    Abstract: An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, and a tip shelf. The suction surface and the pressure surface both extend axially to connect the leading edge to the trailing edge. The suction surface and the pressure surface both extend radially from a root section of the airfoil a tip section of the airfoil. The tip shelf is formed along the tip section, and includes a triangular pocket.

    Abstract translation: 翼型件包括前缘，后缘，吸力表面，压力表面和尖端架。 吸力表面和压力表面都轴向延伸，以将前缘连接到后缘。 抽吸表面和压力表面都从翼型的根部径向延伸到翼型的尖端部分。 尖端架沿着尖端部分形成，并且包括三角形袋。

    SHARK-BITE TIP SHELF COOLING CONFIGURATION
    9.
    发明专利
    SHARK-BITE TIP SHELF COOLING CONFIGURATION 未知

    公开(公告)号：SG11201404131PA

    公开(公告)日：2014-09-26

    申请号：SG11201404131P

    申请日：2013-03-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： QUACH SAN

    IPC: F01D5/30 ,  F01D11/00 ,  F02C7/14 ,  F02K3/00

    Abstract: An airfoil includes a leading edge, a trailing edge, a suction surface, a pressure surface, and a tip shelf. The suction surface and the pressure surface both extend axially to connect the leading edge to the trailing edge. The suction surface and the pressure surface both extend radially from a root section of the airfoil a tip section of the airfoil. The tip shelf is formed along the tip section, and includes a triangular pocket.

    TURBINE ENGINE TRANSMISSION GUTTER
    10.
    发明公开
    TURBINE ENGINE TRANSMISSION GUTTER 审中-公开
    传输通道涡轮发动机

    公开(公告)号：EP2893167A4

    公开(公告)日：2015-10-28

    申请号：EP13835636

    申请日：2013-08-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： NGUYENLOC FRED ,  QUACH SAN

    IPC: F02C7/00 ,  F02C7/36 ,  F02K3/00

    CPC classification number: F01D25/18 ,  F01D15/12 ,  F01D25/24 ,  F05D2260/602 ,  F16H57/0409 ,  F16H57/0423 ,  F16H57/0441 ,  F16H57/045 ,  F16N31/02

    Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.

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