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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。

    REVERSIBLE BLADE DAMPER
    2.
    发明申请
    REVERSIBLE BLADE DAMPER 审中-公开
    可逆式叶片阻尼器

    公开(公告)号：WO2014107212A3

    公开(公告)日：2014-10-09

    申请号：PCT/US2013065202

    申请日：2013-10-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DONNELL BRANDON S ,  GIRMA YAFET ,  O'DELL GINA C

    IPC: F01D5/22 ,  F01D5/26 ,  F01D11/08

    CPC classification number: F01D5/22 ,  F01D5/26 ,  F01D11/005 ,  F01D11/006 ,  F01D11/008 ,  F05D2260/36

    Abstract: A damper body extends between an axial first end, an opposing axial second end, a first lateral side, and an opposing second lateral side. A first pair of lugs are disposed at the first axial end and a second pair of lugs are disposed at the second axial end. In the first lug pair, a lug has an axially outermost foot which extends laterally beyond a lateral wall. The second lug pair has a lug with an axial outermost point with a foot extending laterally beyond a lateral wall. The foot on the first axial end and the foot on the second axial end are on opposed lateral sides.

    Abstract translation: 阻尼体在轴向第一端，相对的轴向第二端，第一侧面和相对的第二侧面之间延伸。 第一对凸耳设置在第一轴向端部，第二对凸耳设置在第二轴向端。 在第一凸耳对中，凸耳具有横向延伸超过侧壁的轴向最外侧的脚。 第二凸耳对具有带轴向最外点的凸耳，其中一个脚横向延伸超过侧壁。 第一轴向端部的脚和第二轴向端部上的脚在相对的侧面上。

    LOST CORE STRUCTURAL FRAME
    3.
    发明申请
    LOST CORE STRUCTURAL FRAME 审中-公开
    失去核心结构框架

    公开(公告)号：WO2015126488A3

    公开(公告)日：2015-11-05

    申请号：PCT/US2014066495

    申请日：2014-11-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TAFFET STEVEN ,  DONNELL BRANDON S ,  NADEAU DANIEL C ,  DEIBEL RUSSELL ,  QUACH SAN

    IPC: B22C9/10 ,  B22C9/22 ,  F01D5/18

    CPC classification number: F01D5/187 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/323 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

    Abstract translation: 失芯模具部件包括第一腿部和第二腿部，第二腿部具有连接第一腿部和第二腿部的多个交叉部件。 多个交叉部件包括彼此间隔开的最外侧交叉部件。 第一支腿和第二支腿中的每一个的相邻末端以及第二交叉构件彼此间隔得比最外侧交叉构件更靠近彼此。 中央交叉部件在第一腿和第二腿之间以及第二交叉部件之间延伸。 最外面的跨接构件延伸第一横截面区域。 第二交叉部件延伸第二横截面区域，并且中央交叉部件延伸第三横截面区域。 第一横截面积大于第二横截面积。 第二横截面积大于第三横截面积。 燃气涡轮发动机和部件也被公开。

    LOST CORE STRUCTURAL FRAME
    6.
    发明公开
    LOST CORE STRUCTURAL FRAME 审中-公开
    STRUKTURRAHMEN MIT VERLORENEM KERN

    公开(公告)号：EP3086893A4

    公开(公告)日：2017-08-23

    申请号：EP14883263

    申请日：2014-11-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TAFFET STEVEN ,  DONNELL BRANDON S ,  NADEAU DANIEL C ,  DEIBEL RUSSELL ,  QUACH SAN

    IPC: B22C9/10 ,  B22C7/02 ,  B22C9/04 ,  B22C9/22 ,  B22C9/24 ,  F01D5/18 ,  F01D9/04

    CPC classification number: F01D5/187 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/323 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

    Abstract translation: 失芯模具部件包括第一腿部和第二腿部，第二腿部具有连接第一腿部和第二腿部的多个交叉部件。 多个交叉部件包括彼此间隔开的最外侧交叉部件。 第一支腿和第二支腿中的每一个的相邻末端以及第二交叉构件彼此间隔得比最外侧交叉构件更靠近彼此。 中央交叉部件在第一腿和第二腿之间以及第二交叉部件之间延伸。 最外面的跨接构件延伸第一横截面区域。 第二交叉部件延伸第二横截面区域，并且中央交叉部件延伸第三横截面区域。 第一横截面积大于第二横截面积。 第二横截面积大于第三横截面积。 燃气涡轮发动机和部件也被公开。

    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    9.
    发明公开
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开
    改进的涡轮螺栓固定器的冷却

    公开(公告)号：EP2877705A4

    公开(公告)日：2015-11-11

    申请号：EP13813721

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/06 ,  F02C7/12

    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.

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