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    LOST CORE STRUCTURAL FRAME
    1.
    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：WO2015126488A2

    公开(公告)日：2015-08-27

    申请号：PCT/US2014/066495

    申请日：2014-11-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    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: 失去的芯模组件包括第一腿部和第二腿部，其具有连接第一和第二腿部的多个交叉构件。 多个交叉构件包括彼此间隔开的最外侧交叉构件。 第一和第二腿部和第二交叉构件中的每一个的相邻端部比最外面的交叉构件彼此更靠近地间隔开。 中央交叉构件在第一和第二腿之间以及第二交叉构件之间延伸。 最外面的交叉构件延伸到第一横截面积。 第二交叉构件延伸到第二横截面积，并且中心交叉构件延伸第三横截面积。 第一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。 还公开了一种燃气涡轮发动机和部件。

    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    3.
    发明申请
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开

    公开(公告)号：WO2014007889A3

    公开(公告)日：2014-01-09

    申请号：PCT/US2013/034220

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： LEVINE, Jeffrey R. ,  MONGILLO, Dominic J. ,  DONNELL, Brandon S.

    IPC: F01D5/18 ,  F02C7/12

    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.

    REVERSIBLE BLADE DAMPER
    5.
    发明申请
    REVERSIBLE BLADE DAMPER 审中-公开
    可逆刀片阻尼器

    公开(公告)号：WO2014107212A2

    公开(公告)日：2014-07-10

    申请号：PCT/US2013/065202

    申请日：2013-10-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： DONNELL, Brandon S. ,  GIRMA, Yafet ,  O'DELL, Gina C.

    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: 缓冲体在轴向第一端，相对轴向第二端，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处，并且第二对凸耳设置在第二轴向端部处。 在第一对花纹块中，花纹块具有横向延伸超过侧壁的轴向最外侧的支脚。 第二个凸耳对具有一个带有轴向最外点的凸耳，并且脚部横向延伸超过侧壁。 在第一轴端上的脚和在第二轴端上的脚在相对的侧面上。

    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    8.
    发明公开
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开
    改进的冷却涡轮叶片后缘

    公开(公告)号：EP2877705A2

    公开(公告)日：2015-06-03

    申请号：EP13813721.1

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： LEVINE, Jeffrey R. ,  MONGILLO, Dominic J. ,  DONNELL, Brandon S.

    IPC: F01D5/18 ,  F02C7/12

    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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