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    DOUBLE WALL TURBINE GAS TURBINE ENGINE BLADE COOLING CONFIGURATION
    5.
    发明申请
    DOUBLE WALL TURBINE GAS TURBINE ENGINE BLADE COOLING CONFIGURATION 审中-公开

    公开(公告)号：US20190169996A1

    公开(公告)日：2019-06-06

    申请号：US15832467

    申请日：2017-12-05

    Applicant: United Technologies Corporation

    Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, JR.

    IPC: F01D5/18 ,  F02C9/18

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. The resupply hole has a single inlet that is fluidly connected to multiple discrete outlet apertures. A centerline of the single inlet is arranged at an angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.

    HOT SECTION ENGINE COMPONENTS HAVING SEGMENT GAP DISCHARGE HOLES
    6.
    发明申请
    HOT SECTION ENGINE COMPONENTS HAVING SEGMENT GAP DISCHARGE HOLES 审中-公开

    公开(公告)号：US20190078441A1

    公开(公告)日：2019-03-14

    申请号：US15699303

    申请日：2017-09-08

    Applicant: United Technologies Corporation

    Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

    IPC: F01D5/18 ,  B23P15/02

    Abstract: Components for gas turbine engines and methods of making the same, the components including a component body having an external side wall and an internal side wall and defining at least a first cooling cavity and a second cooling cavity between the external side wall and the internal side wall, at least one segmented rib extending within the component body and separating the first cooling cavity from the second cooling cavity, wherein the first and second cooling cavities, the at least one segmented rib comprising at least two rib segments separated by a segment gap, and a discharge hole formed in the external side wall fluidly connected the segment gap to an exterior surface of the component body.

    DILUTION HOLE ASSEMBLY
    7.
    发明申请
    DILUTION HOLE ASSEMBLY 有权
    稀释孔组件

    公开(公告)号：US20160003478A1

    公开(公告)日：2016-01-07

    申请号：US14789557

    申请日：2015-07-01

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Stanislav Kostka, JR.

    IPC: F23R3/14 ,  F23R3/00

    CPC classification number: F23R3/14 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A dilution hole assembly that may be of a combustor has a first wall that defines a hole that may communicate through a liner and outer shell of the combustor for flowing dilution air from an air plenum located outward of the shell and into a combustion chamber defined by and located inward of the liner. The assembly has an outer wall that may be engaged to the shell and liner, and which defines the hole. An inner wall of the assembly may be in the hole such that an annular portion of the hole is defined between the inner and outer walls. A plurality of vanes may be in the annular portion and spaced from one-another for swirling air that flows through the annular portion. The walls may be generally conical in shape and/or radially sloped such that air flowing through the annular portion and air flowing at least through the inner portion impinge upon one-another adding to the air turbulence created by the swirling action of the vanes and thus enhancing efficient combustion and temperature profiling within the combustion chamber.

    Abstract translation: 可以是燃烧器的稀释孔组件具有第一壁，其限定可以通过燃烧器的衬套和外壳连通的孔，用于将稀释空气从位于壳体外部的空气室排出并进入由壳体外部限定的燃烧室 并位于内衬的内侧。 组件具有外壁，其可以接合到壳体和衬套，并且限定孔。 组件的内壁可以在孔中，使得孔的环形部分限定在内壁和外壁之间。 多个叶片可以在环形部分中并且彼此间隔开以流过环形部分的旋转空气。 壁可以是大致圆锥形的和/或径向倾斜的，使得流过环形部分的空气和至少通过内部部分流动的空气彼此撞击，从而增加由叶片的旋动作用产生的空气湍流，因此 提高燃烧室内的有效燃烧和温度分布。

    AIRFOIL HAVING ANGLED TRAILING EDGE SLOTS
    9.
    发明申请
    AIRFOIL HAVING ANGLED TRAILING EDGE SLOTS 审中-公开

    公开(公告)号：US20200024967A1

    公开(公告)日：2020-01-23

    申请号：US16052730

    申请日：2018-08-02

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Kevin D. Tracy ,  Dominic J. Mongillo, JR.

    IPC: F01D5/18 ,  F01D9/04

    Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity defined within the airfoil body at the trailing edge, and a plurality of angled pedestals arranged along the trailing edge, wherein the plurality of angled pedestals define a plurality of angled trailing edge slots therebetween. Adjacent angled pedestals of the plurality of angled pedestals define a meter section of a respective angled trailing edge slot and a diffuser section of the respective angled trailing edge slot, wherein the meter section is defined by parallel sides of the adjacent angled pedestals, wherein the parallel sides of the adjacent angled pedestals are oriented at a bleed direction that is less than 90° with respect to a feed direction through the cooling cavity.

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