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    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    1.
    发明申请
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开
    改进的冷却涡轮机空运货物边缘

    公开(公告)号：WO2014007889A2

    公开(公告)日：2014-01-09

    申请号：PCT/US2013034220

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LEVINE JEFFREY R ,  MONGILLO DOMINIC J ,  DONNELL BRANDON S

    CPC classification number: F01D5/187 ,  F01D5/145 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/12 ,  F05D2260/202

    Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.

    Abstract translation: 一种用于燃气涡轮发动机的组件包括第一平台和从第一平台延伸的翼型件。 翼型件包括第一圆角，压力侧偏压排出口和第一中心冷却排出口。 翼型件的压力侧壁和第一平台在后缘处形成锐角。 第一圆角围绕机翼的周边形成，其中翼型件从第一平台延伸。 压力侧偏压的冷却排出口沿着第一圆角外侧的后缘。 每个压力侧偏压的冷却排放口从后缘沿压力侧壁延伸。 第一中心冷却排出口沿着后缘延伸​​到第一圆角中并且位于压力侧壁和吸力侧壁之间的中心。

    EDM METHOD FOR MULTI-LOBED COOLING HOLE
    2.
    发明申请
    EDM METHOD FOR MULTI-LOBED COOLING HOLE 审中-公开
    多孔冷却孔的电火花加工方法

    公开(公告)号：WO2013165511A3

    公开(公告)日：2014-01-03

    申请号：PCT/US2013025716

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LEVASSEUR GLENN ,  PIETRASZKIEWICZ EDWARD F ,  ZELESKY MARK F ,  MONGILLO DOMINIC J ,  KLINEFELTER KEVIN J ,  DOLL STEPHEN D ,  FRITCH MARKUS W

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

    CPC classification number: B23H9/10 ,  B23H1/00 ,  B23H7/26 ,  B23H9/14 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.

    Abstract translation: 用于形成从壁的第一表面上的入口延伸到壁的第二表面上的出口的冷却孔的方法包括：通过放电加工形成冷却孔的扩散部分和出口上的后缘， 并在扩散段中形成纵向凸起。 计量部分从壁的第一表面上的入口延伸到壁的第二表面。 扩散部分从出口延伸到位于入口和出口之间的计量部分的一端。 出口在后缘处基本上是线性的或凸起的，并且叶片由纵向脊部分开。

    FAN COOLING HOLE ARRAY
    3.
    发明申请
    FAN COOLING HOLE ARRAY 审中-公开
    风扇冷却孔阵列

    公开(公告)号：WO2015163949A2

    公开(公告)日：2015-10-29

    申请号：PCT/US2015010010

    申请日：2015-01-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： THORNTON LANE ,  DEVORE MATTHEW A ,  MONGILLO DOMINIC J ,  GAUTSCHI STEVEN BRUCE

    IPC: F01D5/18

    CPC classification number: F01D5/186 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2250/14 ,  F05D2250/312 ,  F05D2250/313 ,  F05D2250/314 ,  F05D2250/324 ,  F05D2250/38 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.

    Abstract translation: 燃气涡轮发动机部件包括翼型，翼型具有从前缘延伸到后缘的吸入侧和压力侧。 在前缘附近有多个冷却孔，冷却孔具有非圆形形状，具有较长的尺寸和较小的尺寸。 翼型限定从径向外端到径向内端的径向方向，并且径向外部的朝向径向外端间隔开的冷却孔具有更接近平行于径向方向延伸的较长尺寸。 与径向外部冷却孔相比，更靠近具有较长尺寸的径向内端的径向内部冷却孔延伸到相对于径向方向更接近垂直。

    GAS TURBINE ENGINE COMPONENT HAVING TRIP STRIPS
    4.
    发明申请
    GAS TURBINE ENGINE COMPONENT HAVING TRIP STRIPS 审中-公开
    具有牵引车的气体涡轮发动机部件

    公开(公告)号：WO2015023338A3

    公开(公告)日：2015-05-14

    申请号：PCT/US2014039350

    申请日：2014-05-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  MONGILLO DOMINIC J

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

    CPC classification number: F01D5/188 ,  F01D5/02 ,  F01D5/189 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: Disclosed is a gas turbine engine including a compressor section and a turbine section. The gas turbine engine includes a gas turbine engine component having a first wall providing an outer surface of the gas turbine engine component and a second wall spaced-apart from the first wall. The first wall is a gas-path wall exposed to a core flow path of the gas turbine engine. The second wall is a non-gas-path wall. A cooling passageway is provided between the second wall and the first wall. The second wall has a trip strip provided thereon.

    Abstract translation: 公开了一种燃气涡轮发动机，其包括压缩机部和涡轮部。 燃气涡轮发动机包括燃气涡轮发动机部件，其具有提供燃气涡轮发动机部件的外表面的第一壁和与第一壁间隔开的第二壁。 第一壁是暴露于燃气涡轮发动机的核心流动路径的气体通道壁。 第二个墙是非气道壁。 在第二壁和第一壁之间设置冷却通道。 第二壁具有设置在其上的跳闸条。

    COOLED TURBINE AIRFOIL
    5.
    发明专利
    COOLED TURBINE AIRFOIL 未知

    公开(公告)号：CA2500503A1

    公开(公告)日：2005-11-06

    申请号：CA2500503

    申请日：2005-03-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GREGG SHAWN J ,  MERCADANTE RUTHANN ,  MONGILLO DOMINIC J

    IPC: F01D20060101 ,  F01D5/00 ,  F01D5/12 ,  F01D5/14 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F02C7/00 ,  F02C7/16

    Abstract: According to the present invention, a hollow airfoil is provided that comprises a leading edge wall portion, a plurality of cavities, one or more crossover ribs, a plurality of cooling apertures, and a plurality of impingement ribs. The cavities are disposed adjacent the leading edge wall portion, between the leading edge wall portion and a first rib. The crossover ribs extend between the leading edge wall portion and the first ri b, and at least one crossover rib is disposed between a pair of the cavities. The cooling apertures are disposed in the leading edge wall portion, providing a passage through which cooling air can exit the cavities. The impingement apertures are disposed in the first rib, providing a passage through which cooling air can enter the cavities. At least one of th e impingement apertures is contiguous with one of the crossover ribs.

    ANGLED TRIPPED AIRFOIL PEANUT CAVITY
    8.
    发明专利
    ANGLED TRIPPED AIRFOIL PEANUT CAVITY 未知

    公开(公告)号：SG150426A1

    公开(公告)日：2009-03-30

    申请号：SG2008029324

    申请日：2008-04-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHON YOUNG H ,  MONGILLO DOMINIC J ,  PROPHETER-HINCKLEY TRACY A ,  JOSEPH W BRIDGES JR

    Abstract: ANGLED TRIPPED AIRFOIL PEANUT CAVITY A turbine airfoil comprises a wall portion, a cooling channel, an impingement rib, impingement rib nozzles, turbulators and leading edge cooling holes. The wall portion comprises a leading edge, a trailing edge, an outer diameter end, and an inner diameter end. The cooling channel receives cooling air and extends through an interior of the wall portion between the inner diameter end and the outer diameter end. The impingement rib is positioned within the wall portion forward of the cooling channel and between the outer diameter end and the inner diameter end to define a peanut cavity. The impingement rib nozzles extend through the impingement rib for receiving cooling air from the cooling channel. The turbulators are positioned within the peanut cavity to locally influence the flow of the cooling air. The leading edge cooling holes discharge the cooling air from the peanut cavity to an exterior of the wall portion.

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