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    AIRFOIL HAVING FORWARD FLOWING SERPENTINE FLOW
    32.
    发明申请
    AIRFOIL HAVING FORWARD FLOWING SERPENTINE FLOW 审中-公开

    公开(公告)号：US20190048729A1

    公开(公告)日：2019-02-14

    申请号：US15671351

    申请日：2017-08-08

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/02 ,  F01D25/12

    Abstract: Airfoils including an airfoil body having leading and trailing edges and root and tip regions, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from the root region to the tip region, a forward-flowing serpentine flow path within the airfoil body defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity, a flag tip cavity extending aftward from proximate the leading edge to the trailing edge along the tip region, and a hybrid trailing edge cavity, wherein the first serpentine cavity is part of the hybrid trailing edge cavity and cooling air is supplied into the forward-flowing serpentine flow path from a hybrid trailing edge feed cavity inlet.

    AFT FLOWING SERPENTINE CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINES
    34.
    发明申请
    AFT FLOWING SERPENTINE CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINES 审中-公开

    公开(公告)号：US20180156045A1

    公开(公告)日：2018-06-07

    申请号：US15368746

    申请日：2016-12-05

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom having an aft flowing serpentine hybrid skin core positioned relative to a plurality of core bodies and configured to define at least one serpentine cavity within the manufactured airfoil. The aft flowing serpentine hybrid skin core extends from a root region toward a tip region in a radial direction of the manufactured airfoil and the plurality of core bodies are positioned about the aft flowing serpentine hybrid skin core to form a shielding structure to thermally shield the aft flowing serpentine hybrid skin core in the manufactured airfoil.

    LEADING EDGE HYBRID CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINE
    35.
    发明申请
    LEADING EDGE HYBRID CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180156043A1

    公开(公告)日：2018-06-07

    申请号：US15368737

    申请日：2016-12-05

    Applicant: United Technologies Corporation

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

    IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  B22C9/04 ,  B22C9/10

    Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom, the core assemblies having a leading edge hybrid skin core positioned relative to a plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil. The leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.

    GAS TURBINE ENGINE AIRFOIL WITH LARGE THICKNESS PROPERTIES
    38.
    发明申请
    GAS TURBINE ENGINE AIRFOIL WITH LARGE THICKNESS PROPERTIES 审中-公开
    具有大的厚度特性的气体涡轮发动机气动翼

    公开(公告)号：US20150354365A1

    公开(公告)日：2015-12-10

    申请号：US14728514

    申请日：2015-06-02

    Applicant: United Technologies Corporation

    Inventor： Wolfgang Balzer ,  Thomas J. Praisner ,  Atul Kohli ,  Mark F. Zelesky ,  Dominic J. Mongillo, JR.

    IPC: F01D5/14 ,  F01D5/18 ,  F01D5/02

    Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord 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包括具有压力和吸力侧面的翼型件，其在前缘和后缘处接合。 翼型件从支撑件沿径向方向延伸跨度。 0％跨度和100％跨度位置分别对应于支撑件和末端处的翼型。 前缘和后缘在轴向上彼此间隔开一个轴向弦。 在跨距位置处的翼型件的横截面具有与压力侧和吸力侧相切的直径。 直径对应于横截面内最大的圆形配件。 直径与轴向弦的比例在50％至95％的跨度位置之间至少为0.4。

    TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING
    39.
    发明申请
    TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING 有权
    TURBINE AIRFOIL TIP SHELF和SQUEALER POCKET COOLING

    公开(公告)号：US20150292334A1

    公开(公告)日：2015-10-15

    申请号：US14748666

    申请日：2015-06-24

    Applicant: United Technologies Corporation

    Inventor： Dominic J. Mongillo, JR. ,  Steven Bruce Gautschi ,  San Quach

    IPC: F01D5/14 ,  F01D5/18

    CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.

    Abstract translation: 翼型件包括压力表面和从翼型件的根部部分延伸到翼型件的尖端部分的抽吸表面。 翼型件还包括前缘和后缘，其在它们之间限定翼型的翼弦长度。 所述翼型件还包括沿所述翼型件的所述尖端部分在所述压力表面和尖端搁板壁之间形成的尖端架。 尖端架壁在压力表面和吸力表面之间间隔开，并且尖端架从从前缘测量的弦长的10％范围内延伸到从后缘测量的弦长的10％以内。

    TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING
    40.
    发明申请
    TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING 有权
    TURBINE AIRFOIL TIP SHELF和SQUEALER POCKET COOLING

    公开(公告)号：US20150118063A1

    公开(公告)日：2015-04-30

    申请号：US14250166

    申请日：2014-04-10

    Applicant: United Technologies Corporation

    Inventor： Scott D. Lewis ,  Dominic J. Mongillo, JR. ,  Steven Bruce Gautschi ,  Christopher Corcoran

    IPC: F01D5/20 ,  F01D5/18

    CPC classification number: F01D5/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge.

    Abstract translation: 翼型件包括从根部延伸到翼型的尖端部分的压力和吸力表面。 翼型件还包括在其间限定弦长的前缘和后缘。 沿着压力表面和尖端搁板壁之间的尖端部分形成尖端搁板，顶部搁板壁在压力表面和吸力表面之间分开。 沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。 尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。 尖叫口袋从前缘测量的弦长的10％范围内延伸，以终止从后缘测得的弦长不到85％。

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