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    GAS TURBINE ENGINE COMPONENT MATEFACE SURFACES
    1.
    发明申请
    GAS TURBINE ENGINE COMPONENT MATEFACE SURFACES 审中-公开
    燃气轮机发动机部件表面粗糙度曲面

    公开(公告)号：WO2015088699A8

    公开(公告)日：2015-06-18

    申请号：PCT/US2014/065430

    申请日：2014-11-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： LEWIS, Scott D. ,  KOHLI, Atul ,  PRAISNER, Thomas J.

    IPC: F01D25/00 ,  F01D5/14 ,  F01D5/22 ,  F01D5/30 ,  F01D9/02 ,  F01D11/08

    Abstract: An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.

    Abstract translation: 燃气涡轮发动机中的部件阵列包括第一结构和第二结构，第一结构和第二结构分别包括彼此相邻布置以提供间隙的第一表面和第二表面。 第一和第二表面分别在间隙处具有第一和第二圆形边缘，这些边缘相对于彼此以交错关系布置。

    GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES
    2.
    发明申请
    GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES 审中-公开
    气体涡轮发动机中间涡轮机框架与流动特性

    公开(公告)号：WO2013115871A1

    公开(公告)日：2013-08-08

    申请号：PCT/US2012/063837

    申请日：2012-11-07

    Applicant: UNITED TECHNOLOGIES CORPORATION ,  PRAISNER, Thomas J. ,  MAGGE, Shankar S. ,  ESTES, Matthew B.

    Inventor： PRAISNER, Thomas J. ,  MAGGE, Shankar S. ,  ESTES, Matthew B.

    IPC: F01D9/04 ,  F02C3/04

    CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D9/04 ,  F01D9/065 ,  F01D25/28 ,  F02K3/06 ,  F05D2240/12 ,  Y02T50/673

    Abstract: A gas turbine engine includes first and second stages having a rotational axis. A mid turbine frame is arranged axially between the first and second stages. The mid turbine frame includes a circumferential array of airfoils, and the airfoils each have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°, for example. In one example, an airfoil aspect ratio is less than 1.5.

    Abstract translation: 燃气涡轮发动机包括具有旋转轴线的第一和第二级。 中间涡轮机框架轴向布置在第一和第二阶段之间。 中间涡轮机框架包括圆周阵列的翼型件，翼型件各自具有在压力侧和吸力侧之间等距离设置的曲率。 翼型件沿着翼型在中跨平面处从前缘延伸到后缘。 在与翼面前缘和后缘处的平面和曲率的交点相切的第一和第二线之间限定角度。 该角度例如等于或大于约10°。 在一个示例中，翼型长宽比小于1.5。

    LOW LOSS AIRFOIL PLATFORM TRAILING EDGE
    4.
    发明申请
    LOW LOSS AIRFOIL PLATFORM TRAILING EDGE 审中-公开
    低损失航空平台行驶边

    公开(公告)号：WO2013130181A2

    公开(公告)日：2013-09-06

    申请号：PCT/US2013/020962

    申请日：2013-01-10

    Applicant: UNITED TECHNOLOGIES CORPORATION ,  AGGARWALA, Andrew S. ,  PRAISNER, Thomas J.

    Inventor： AGGARWALA, Andrew S. ,  PRAISNER, Thomas J.

    IPC: F01D5/20 ,  F01D5/14

    CPC classification number: F01D5/143 ,  F05D2240/80 ,  F05D2260/60 ,  Y02T50/673

    Abstract: An airfoil platform comprises a leading edge portion and a trailing edge portion. The trailing edge portion comprises a first region having a convex flowpath contour, a second region having an intermediate flowpath contour extending downstream from the convex flowpath contour, and a third region having a concave or linear flowpath contour extending downstream from the intermediate flowpath contour to a downstream end of the trailing edge portion of the platform.

    Abstract translation: 翼型平台包括前缘部分和后缘部分。 后缘部分包括具有凸形流路轮廓的第一区域，具有从凸形流路轮廓的下游延伸的中间流路轮廓的第二区域以及具有从中间流路轮廓向下延伸的凹或线性流路轮廓的第三区域 平台的后缘部分的下游端。

    STATOR VANE ASSEMBLY AND METHOD THEREFORE
    5.
    发明申请
    STATOR VANE ASSEMBLY AND METHOD THEREFORE 审中-公开
    定子风扇组件及其方法

    公开(公告)号：WO2014130214A1

    公开(公告)日：2014-08-28

    申请号：PCT/US2014/013276

    申请日：2014-01-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： FARAH, Jorge I. ,  BURT, Jonathan P. ,  PRAISNER, Thomas J.

    IPC: F01D9/02 ,  F02C7/00

    CPC classification number: F01D9/047 ,  F01D25/162 ,  F02C7/20 ,  F05D2230/23 ,  F05D2240/12 ,  F05D2240/80

    Abstract: A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.

    Abstract translation: 定子叶片组件包括多个不同的叶片段，每个叶片段分别包括第一平台，第二平台和至少一个叶片翼型件，其相对的端部连接到第一平台和第二平台。 第一平台在不同的第一接头彼此相交，并且第二平台在彼此不同的第二接头处相交，使得多个叶片段形成环形结构。

    GEARED TURBOFAN WITH THREE TURBINES ALL CO-ROTATING
    8.
    发明申请
    GEARED TURBOFAN WITH THREE TURBINES ALL CO-ROTATING 审中-公开
    具有三轮涡轮机的所有旋转齿轮

    公开(公告)号：WO2013165862A1

    公开(公告)日：2013-11-07

    申请号：PCT/US2013/038560

    申请日：2013-04-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard ,  PRAISNER, Thomas J.

    IPC: F02K3/04

    CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2260/40311

    Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.

    Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮驱动风扇通过齿轮减速。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 高速滑阀，中速滑阀和风扇驱动涡轮机构造成沿相同的第一方向旋转。

    STRUT FOR A GAS TURBINE ENGINE
    9.
    发明公开
    STRUT FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3543463A3

    公开(公告)日：2019-10-16

    申请号：EP19164615.7

    申请日：2019-03-22

    Applicant: United Technologies Corporation

    Inventor： EASTWOOD, Jonathan Jeffery ,  MEMORY, Curtis L. ,  HU, Jin ,  PRAISNER, Thomas J.

    IPC: F01D5/14 ,  F01D9/06 ,  F01D25/30

    Abstract: A strut (66) for a gas turbine engine includes an airfoil section (67) extending in a spanwise direction (R) between a first platform (64P) and a second platform (62P), extending in a chordwise direction (C) between a leading edge (82) and trailing edge to define a chord length, and extending in a thickness direction (T) between a first side and a second side to define a chord width. Exterior surfaces of the airfoil section (67) define a leading portion (68) between the leading edge (82) and a widest location of the airfoil section (67) relative to the thickness direction (T), and a trailing portion (70) between the widest location and the trailing edge. The exterior surfaces establish a respective exterior contour for each span position between a 0% span position and a 100% span position. The exterior surfaces define a plurality of dimples (72) in the leading portion (68).

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