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    GAS TURBINE ENGINE AIRFOIL WITH SHOWERHEAD COOLING HOLES NEAR LEADING EDGE
    31.
    发明公开
    GAS TURBINE ENGINE AIRFOIL WITH SHOWERHEAD COOLING HOLES NEAR LEADING EDGE 审中-公开
    带有喷头冷却孔的燃气涡轮发动机机翼接近边缘

    公开(公告)号：EP3296512A1

    公开(公告)日：2018-03-21

    申请号：EP17191316.3

    申请日：2017-09-15

    Applicant: United Technologies Corporation

    Inventor： LEWIS, Scott D. ,  MONGILLO, Dominic J. ,  KOHLI, Atul

    IPC: F01D5/18

    Abstract: An airfoil (78) for a gas turbine engine (20) includes pressure and suction side walls (86,88) joined to one another at leading and trailing edges (82,84) to provide an exterior airfoil surface. The pressure and suction side walls (86,88) are spaced apart from one another in a thickness direction (T). A stagnation line (83) is located near the leading edge (82). A cooling passage is provided between the pressure and suction side walls. Showerhead cooling holes (100) are arranged at least one of adjacent to or on the stagnation line (83). At least one of the showerhead cooling holes (100) has a metering hole fluidly connecting the cooling passage to a diffuser arranged at the exterior airfoil surface. At least one showerhead cooling hole (100) is arranged on each of opposing sides of the stagnation line (83). Each showerhead cooling hole (100) has the diffuser with a first diffuser angle that expands downstream in the thickness direction (T) in opposing directions from one another when separated by the stagnation line (83).

    Abstract translation: 用于燃气涡轮发动机（20）的翼型（78）包括在前缘和后缘（82,84）处彼此连接以提供外翼型表面的压力侧壁和吸力侧壁（86,88）。 压力和吸入侧壁（86,88）在厚度方向（T）上彼此间隔开。 停滞线（83）位于前缘（82）附近。 在压力侧壁和吸入侧壁之间设有冷却通道。 喷淋头冷却孔（100）布置在相邻或停滞线（83）上或其中的至少一个上。 喷淋头冷却孔（100）中的至少一个具有将冷却通道流体连接到布置在外部翼型表面上的扩散器的计量孔。 至少一个喷头冷却孔（100）布置在停滞线（83）的相对侧中的每一侧上。 每个喷头冷却孔（100）具有扩散器，该扩散器具有第一扩散角度，该第一扩散角度在被滞流线（83）分开时沿厚度方向（T）在彼此相反的方向上向下游扩展。

    BAFFLE INSERT FOR A GAS TURBINE ENGINE COMPONENT AND METHOD OF COOLING
    32.
    发明公开
    BAFFLE INSERT FOR A GAS TURBINE ENGINE COMPONENT AND METHOD OF COOLING 审中-公开
    燃气涡轮发动机组件的挡板插件和冷却方法

    公开(公告)号：EP3181818A1

    公开(公告)日：2017-06-21

    申请号：EP16202734.6

    申请日：2016-12-07

    Applicant: United Technologies Corporation

    Inventor： SPANGLER, Brandon W. ,  KOHLI, Atul

    IPC: F01D5/18

    CPC classification number: F02C7/18 ,  F01D5/18 ,  F01D5/188 ,  F01D25/08 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/22141

    Abstract: A method of increasing a heat transfer of a cooling fluid passing through a component of a gas turbine engine. The method including the steps of: directing a cooling fluid between an interior surface (36) of an internal cooling cavity (26) of the component and an exterior surface of a baffle insert (32) located in the internal cooling cavity; and creating a plurality of vortices in the cooling fluid as it passes between the exterior surface of the baffle insert and the interior surface of the internal cooling cavity, wherein the internal cooling cavity is elliptical in shape and/or wherein the exterior surface of the baffle insert is elliptical in shape.

    Abstract translation: 一种增加通过燃气涡轮发动机的部件的冷却流体的传热的方法。 该方法包括以下步骤：在部件的内部冷却腔体（26）的内表面（36）与位于内部冷却腔体中的挡板插入件（32）的外表面之间引导冷却流体; 以及在冷却流体通过挡板插入件的外表面和内部冷却腔的内表面之间时在冷却流体中产生多个涡流，其中内部冷却腔的形状为椭圆形和/或其中挡板的外表面 插入物是椭圆形的。

    GAS TURBINE ENGINE COMPONENT AND WALL
    34.
    发明公开
    GAS TURBINE ENGINE COMPONENT AND WALL 审中-公开
    GASTURBINENKRAFTWERKSBAUTEIL UND-WAND

    公开(公告)号：EP2985417A1

    公开(公告)日：2016-02-17

    申请号：EP15180911.8

    申请日：2015-08-13

    Applicant: United Technologies Corporation

    Inventor： XU, Jinquan ,  KOHLI, Atul ,  MONGILLO, Dominic J ,  LEVASSEUR, Glenn ,  ZELESKY, Mark F

    IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F23R3/06

    CPC classification number: F01D5/189 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component (80; 84) has a cooling hole (82; 86; 106) with a metering section (114). The metering section (114) includes a convex surface (300; 400) and a concave surface (310; 410), with a first arcuate channel (320; 420) connecting an end (301) of the convex surface (300; 400) and an end (311) of the concave surface (310; 410). The end (301) of the convex surface (300; 400) and the end (311) of the concave surface (310; 410) define a dimension (D 1 ) that is smaller than a diameter (D) of the arcuate channel (320; 420).

    Abstract translation: 燃气涡轮发动机部件（80; 84）具有带有计量部分（114）的冷却孔（82; 86; 106）。 计量部分（114）包括凸表面（300; 400）和凹表面（310; 410），其中连接凸表面（300; 400）的端部（301）的第一弧形通道（320; 420） 和凹面（310; 410）的端部（311）。 凸表面（300; 400）的端部（301）和凹面（310; 410）的端部（311）限定了小于弧形通道（D）的尺寸（D 1） 320; 420）。

    AIRFOIL WITH VARYING WALL THICKNESS
    37.
    发明公开
    AIRFOIL WITH VARYING WALL THICKNESS 审中-公开

    公开(公告)号：EP3533971A1

    公开(公告)日：2019-09-04

    申请号：EP19160627.6

    申请日：2019-03-04

    Applicant: United Technologies Corporation

    Inventor： KOHLI, Atul ,  GHIGLIOTTY, Jaime G. ,  DOWNEY, James B.

    IPC: F01D5/18

    Abstract: An airfoil (60) includes an airfoil body (62) that has a peripheral wall (64) that defines an exterior side (64a) and an interior side (64b) that bounds an internal cavity (66) in the airfoil body (62). The peripheral wall (64) has first and second wall sections (72, 74) joined by a transition section (76). The first wall section (72) is thicker than the second wall section (74). The transition section (76) provides a change in thickness between the first wall section (72) and the second wall section (74). The second wall section (74) includes a cooling hole (78) that has a first end that opens to the internal cavity (66) at the interior side (64b) and a second end that opens to the exterior side (64a).

    PRESSURE EQUALIZING ORIFICE FOR BAFFLES IN VANES
    38.
    发明公开
    PRESSURE EQUALIZING ORIFICE FOR BAFFLES IN VANES 审中-公开

    公开(公告)号：EP3409896A1

    公开(公告)日：2018-12-05

    申请号：EP18164585.4

    申请日：2018-03-28

    Applicant: United Technologies Corporation

    Inventor： SPANGLER, Brandon W. ,  KOHLI, Atul

    IPC: F01D9/06

    Abstract: Module for a gas turbine engine including: a disk (108) rotatable about an engine central axis (A) and a vane (106) fixedly disposed upstream of the disk (108), the vane (106) being hollow and including a vane cavity (122) having a vane longitudinal span between a vane upstream opening and vane downstream opening, the vane (106) including: a baffle (130) fixedly supported within the vane cavity (122), the baffle (130) having a hollow interior (129) and a longitudinal span between a baffle upstream surface and a baffle downstream surface, the baffle longitudinal span being less than the vane longitudinal span; wherein a baffle opening area fluidly connects the vane cavity (122) to the baffle interior (129), the baffle opening area is between 32 x 10 -5 square centimetres (5.0 x 10^-5 square inches) and 9.7 x 10 -3 square centimetres (1.5 x 10^-3 square inches).

    TURBINE COMPONENT WITH TIP FILM COOLING AND METHOD OF COOLING
    39.
    发明公开
    TURBINE COMPONENT WITH TIP FILM COOLING AND METHOD OF COOLING 审中-公开

    公开(公告)号：EP3406852A1

    公开(公告)日：2018-11-28

    申请号：EP18174180.2

    申请日：2018-05-24

    Applicant: United Technologies Corporation

    Inventor： MONGILLO, Dominic J. ,  BALZER, Wolfgang ,  KOHLI, Atul

    IPC: F01D5/20

    Abstract: In one embodiment, a component (74) for a gas turbine engine is provided. The component including: an airfoil (78) having a tip portion (88); a tip shelf (90) located in the tip portion; a first plurality of cooling openings (94) located in an edge of the tip shelf that extends along at least a portion of a pressure side of the airfoil; and a second plurality of cooling openings (104) located in an edge of the tip portion proximate to the tip shelf that extends along at least a portion of the pressure side of the tip portion.

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