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    GAS TURBINE ENGINE ROTOR INCLUDING SQUEALER TIP POCKET
    41.
    发明申请
    GAS TURBINE ENGINE ROTOR INCLUDING SQUEALER TIP POCKET 审中-公开

    公开(公告)号：US20170350255A1

    公开(公告)日：2017-12-07

    申请号：US15175108

    申请日：2016-06-07

    Applicant: United Technologies Corporation

    Inventor： Patrick D. Couture ,  Scott D. Lewis ,  Kyle C. Lana

    IPC: F01D5/18 ,  F02C3/04

    Abstract: A gas turbine engine blade includes a blade portion having a leading edge and a trailing edge. A first surface connects the leading edge to the trailing edge and a second surface connects the leading edge to the trailing edge. A tip section is located at a first end of the blade portion and includes a pocket protruding into the tip section from an outermost end of the tip section. The pocket has a first side wall adjacent the first surface and a second side wall adjacent the second surface. At least one of the first side wall and the second side wall have a curve distinct from a curve of the corresponding adjacent surface.

    AIRFOIL IMPINGEMENT CAVITY
    44.
    发明申请
    AIRFOIL IMPINGEMENT CAVITY 审中-公开
    航空运动舱

    公开(公告)号：US20160333701A1

    公开(公告)日：2016-11-17

    申请号：US14710397

    申请日：2015-05-12

    Applicant: United Technologies Corporation

    Inventor： Scott D. Lewis ,  Christopher Corcoran

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2250/11 ,  F05D2250/13 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/183 ,  F05D2260/201 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: An airfoil having one-sided pedestals is disclosed. The airfoil may define various cavities, such as an inflow feed cavity, an impingement cavity, and an outflow cavity. The various cavities may be connected by crossover sections such as an inflow crossover section and an outflow crossover section. Cooling air may be conducted into the inflow feed cavity, out of the inflow feed cavity through an inflow crossover section into an impingement cavity, and through an impingement cavity. The cooling air may be conducted out of the impingement cavity and into an outflow cavity through an outflow crossover section. Various cavities may include one-wall pedestals. One-wall pedestals may be structures extending from a wall of a cavity into the void of the cavity, whereupon cooling air may impinge, effectuating convective cooling.

    Abstract translation: 公开了具有单面基座的翼型件。 翼型件可以限定各种空腔，例如流入进料腔，冲击腔和流出腔。 各种空腔可以通过交叉部分连接，例如流入交叉部分和流出交叉部分。 冷却空气可以通过流入交叉部分进入入口进料腔，从流入进料腔中进入冲击腔，并通过冲击腔。 冷却空气可以通过流出交叉部分被从冲击腔导入流出腔。 各种空腔可以包括单壁基座。 单壁基座可以是从空腔壁延伸到空腔的结构，于是冷却空气可能会撞击，从而实现对流冷却。

    MATEFACE SURFACES HAVING A GEOMETRY ON TURBOMACHINERY HARDWARE
    46.
    发明申请
    MATEFACE SURFACES HAVING A GEOMETRY ON TURBOMACHINERY HARDWARE 审中-公开
    具有涡轮机硬件几何特性的表面表面

    公开(公告)号：US20160201469A1

    公开(公告)日：2016-07-14

    申请号：US14914762

    申请日：2014-08-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Scott D. Lewis ,  John W. Magowan

    IPC: F01D5/14 ,  F01D25/12 ,  F01D9/04 ,  F01D5/02 ,  F01D5/18

    Abstract: Turbomachinery hardware, used in a rotor assembly and a stator assembly, including an airfoil portion including a leading edge, a trailing edge, a pressure side, and a suction side, and a platform on which the airfoil portion is disposed. The platform including a platform axis, a pressure side mateface located adjacent to the pressure side of the airfoil portion and a suction side mateface located adjacent to the suction side airfoil portion, wherein a portion of a pressure side mateface includes a first geometry, and a portion of a suction side mateface includes a second geometry. The first geometry is selected from a group consisting of: oblique to a platform axis, and a first curved portion. The second geometry is selected from a group consisting of: oblique to the platform axis and a second curved portion.

    Abstract translation: 用于转子组件和定子组件的涡轮机械硬件，包括包括前缘，后缘，压力侧和吸力侧的翼型部分，以及设置翼型部分的平台。 所述平台包括平台轴线，位于所述翼型部分的压力侧附近的压力侧配合件和邻近所述吸入侧翼型部分的吸力侧面板，其中压力侧面部分包括第一几何形状，以及 抽吸侧面的一部分包括第二几何形状。 第一几何形状选自由以下部分组成的组：倾斜于平台轴线和第一弯曲部分。 第二几何形状选自：倾斜于平台轴线和第二弯曲部分的组。

    Turbine airfoil tip shelf and squealer pocket cooling
    47.
    发明授权
    Turbine airfoil tip shelf and squealer pocket cooling 有权
    涡轮机翼尖架和尖叫口袋冷却

    公开(公告)号：US09284845B2

    公开(公告)日：2016-03-15

    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

    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的85％以下。

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