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    INTERNAL COOLING CAVITY WITH TRIP STRIPS
    21.
    发明授权
    INTERNAL COOLING CAVITY WITH TRIP STRIPS 有权
    内部冷却腔与TRIP STRIPS

    公开(公告)号：EP3051064B1

    公开(公告)日：2017-09-13

    申请号：EP15194621.7

    申请日：2015-11-13

    Applicant: United Technologies Corporation

    Inventor： QUACH, San ,  KOHLI, Atul ,  DEVORE, Matthew A. ,  GAUTSCHI, Steven Bruce

    IPC: F01D5/18

    Abstract: An airfoil (200) is provided. The airfoil (200) may comprise a cross over (232), an impingement chamber (230) in fluid communication with the cross over (232), and a first trip strip (236; 260...270) disposed on a first surface (237) of the impingement chamber (230). A cooling system is also provided. The cooling system may comprise an impingement chamber (230), a first trip strip (236; 260...270) on a first surface (237) of the impingement chamber (230), and a second trip strip (238; 280...290) on a second surface (239) of the impingement chamber (230). An internally cooled engine part is further provided. The internally cooled part may comprise a cross over (232) and an impingement chamber (230) in fluid communication with the cross over (232). The cross over (232) may be configured to direct air towards a first surface (237) of the impingement chamber (230). A first trip strip (236; 260...270) may be disposed on the first surface (237) of the impingement chamber (230).

    Abstract translation: 提供翼型件（200）。 翼型件（200）可以包括横跨（232），与横跨（232）流体连通的冲击室（230），以及设置在第一表面上的第一跳闸带（236; 260 ... 270） （230）的内​​表面（237）。 还提供冷却系统。 冷却系统可以包括冲击室（230），在冲击室（230）的第一表面（237）上的第一行程条（236; 260 ... 270）和第二行程条（238; 在冲击室（230）的第二表面（239）上。 还提供了内部冷却的发动机部件。 内部冷却部分可以包括跨越（232）和与跨越（232）流体连通的冲击室（230）。 交叉（232）可以被配置为将空气朝向冲击室（230）的第一表面（237）引导。 第一脱扣条（236; 260 ... 270）可以设置在冲击室（230）的第一表面（237）上。

    GAS TURBINE ENGINE AIRFOIL WITH LARGE THICKNESS PROPERTIES
    23.
    发明公开
    GAS TURBINE ENGINE AIRFOIL WITH LARGE THICKNESS PROPERTIES 审中-公开
    GASTURBINENMOTORSCHAUFEL MIT HOHER DICKE

    公开(公告)号：EP2952683A1

    公开(公告)日：2015-12-09

    申请号：EP15170835.1

    申请日：2015-06-05

    Applicant: United Technologies Corporation

    Inventor： BALZER, Woflgang ,  PRAISNER, Thomas J. ,  KOHLI, Atul ,  ZELESKY, Mark F. ,  MONGILLO Jr., Dominic J.

    IPC: F01D5/14

    CPC classification number: F01D5/141 ,  F01D5/02 ,  F01D5/186 ,  F05D2220/32 ,  F05D2250/10 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673

    Abstract: An airfoil (78) for a gas turbine engine includes an airfoil with pressure and suction sides (94,96) that are joined at leading and trailing edges (82,84). The airfoil (78) extends a span from a support (76) to an end (80) in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil (78) at the support (76) and at the end (80). The leading and trailing edges (82,84) are spaced apart from one another an axial chord (b x ) in an axial direction (X). A cross-section of the airfoil (78) at a span location has a diameter (d max ) tangent to the pressure and suction sides. The diameter (d max ) corresponds to the largest circle fitting within the cross-section. A ratio of the diameter (d max to the axial chord (b x ) is at least 0.4 between 50% and 95% span location.

    Abstract translation: 用于燃气涡轮发动机的翼型件（78）包括具有压力和吸力侧（94,96）的翼型件，其在前缘和后缘（82,84）处接合。 机翼（78）在径向上从支撑件（76）延伸到端部（80）的跨度。 0％跨度和100％跨度位置分别对应于支撑件（76）和端部（80）处的翼型件（78）。 前缘和后缘（82,84）在轴向方向（X）上彼此间隔开轴向弦（b x）。 在跨距位置处的翼型件（78）的横截面具有与压力侧和吸力侧相切的直径（d max）。 直径（d max）对应于横截面内的最大圆形配件。 直径（d max与轴向弦（b x）的比率）在50％至95％跨度位置之间至少为0.4。

    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE
    24.
    发明公开
    COOLING HOLE WITH THERMO-MECHANICAL FATIGUE RESISTANCE 审中-公开
    散热孔与抗病性的热机械疲劳

    公开(公告)号：EP2815103A2

    公开(公告)日：2014-12-24

    申请号：EP13784334.8

    申请日：2013-02-12

    Applicant: United Technologies Corporation

    Inventor： KOHLI, Atul ,  GLEINER, Matthew, S. ,  ZELESKY, Mark, F. ,  XU, JinQuan

    IPC: F02C7/18 ,  F01D25/12 ,  F02K3/00 ,  F01D5/08

    CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe diverging longitudinally and laterally from the metering section, an upstream end located at the outlet, a trailing edge located at the outlet opposite the upstream end and generally opposite first and second sidewalls. Each sidewall has an edge extending along the outlet between the upstream end and the trailing edge. Each edge diverges laterally from the upstream end and converges laterally before reaching the trailing edge.

    TRI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE
    25.
    发明公开
    TRI-LOBED COOLING HOLE AND METHOD OF MANUFACTURE 有权
    BAUTEIL EINES GASTURBINENKRAFTWERKS

    公开(公告)号：EP2815098A1

    公开(公告)日：2014-12-24

    申请号：EP13749073.6

    申请日：2013-02-12

    Applicant: United Technologies Corporation

    Inventor： ZELESKY, Mark, F. ,  KOHLI, Atul ,  LEWIS, Scott, D.

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

    CPC classification number: F23R3/06 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge.

    Abstract translation: 燃气涡轮发动机部件包括第一和第二壁表面，位于第一壁表面处的入口，位于第二壁表面处的出口和位于入口和出口之间的扩散部分。 扩散部分包括第一凸角，与第一凸角相邻的第二凸角和与第二凸角相邻的第三凸角。 第一个叶和第二个小叶在第一个山脊相交，第二个叶和第三个叶在第二个山脊相遇。

    AIRFOIL HAVING END WALL CONTOURED PEDESTALS
    30.
    发明公开
    AIRFOIL HAVING END WALL CONTOURED PEDESTALS 审中-公开

    公开(公告)号：EP3453831A3

    公开(公告)日：2019-05-01

    申请号：EP18182057.2

    申请日：2018-07-05

    Applicant: United Technologies Corporation

    Inventor： SPANGLER, Brandon W. ,  KOHLI, Atul

    IPC: F01D5/18

    Abstract: Airfoils and gas turbine engines having the same, the airfoils including an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity (318) defined within the airfoil body, wherein at least one wall of the cooling cavity is a curved end wall (328), and an end wall contoured pedestal (352) positioned adjacent the curved end wall. The end wall contoured pedestal has a first portion (356) with a contoured side wall (360) and a parallel side wall (358), and a second portion (362) with tapering side walls, wherein the contoured side wall faces the curved end wall, the contoured side wall paralleling a contour of the curved end wall and defining a meter section (354) therebetween.

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