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    Leakage air systems for turbomachines
    21.
    发明授权
    Leakage air systems for turbomachines 有权

    公开(公告)号：US09938842B2

    公开(公告)日：2018-04-10

    申请号：US14601033

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brandon W. Spangler

    IPC: F01D5/18 ,  F01D9/06 ,  F01D9/02 ,  F01D25/12

    CPC classification number: F01D9/065 ,  F01D9/02 ,  F01D25/12 ,  Y02T50/675

    Abstract: A cooling system for a turbomachine includes a vane having an outer diameter platform at one end and an inner diameter platform at another end opposite the outer diameter platform. The outer diameter platform includes outer diameter attachment structure operative to mount the vane to an outer diameter stationary structure. The inner diameter platform is operative to be disposed on an inner diameter stationary structure. The cooling system also includes an airfoil disposed between the outer diameter platform and the inner diameter platform and defining a first cross-passage. The first cross-passage defines a first outer diameter opening in the outer diameter platform. The first cross-passage defines a first inner diameter opening in the inner diameter platform such that a first leakage flow can pass through the vane from the inner diameter platform, through the airfoil, to the outer diameter platform, and into an outer diameter leakage path of the vane.

    Overlapping herringbone filmhole patterned airfoil
    22.
    发明授权
    Overlapping herringbone filmhole patterned airfoil 有权

    公开(公告)号：US09845686B2

    公开(公告)日：2017-12-19

    申请号：US14707875

    申请日：2015-05-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brandon W. Spangler

    IPC: F01D5/18 ,  F01D9/06

    CPC classification number: F01D5/186 ,  F01D9/065 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An airfoil having an overlapping herringbone filmhole pattern is disclosed. For instance, the airfoil may have filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally radially outward over a surface of the airfoil and a second group may be oriented to direct cooling air generally radially inward over a surface of the airfoil. Between the first group and the second group of filmholes in each filmrow, a transition region exists. A transition region filmrow group may be disposed within the transition region and may be co-linear with or staggered relative to the first group and/or the second group. In this manner, the transition region filmrow group enhances the effectiveness of the cooling proximate to the transition region.

    COVER PLATE FOR A COMPONENT OF A GAS TURBINE ENGINE
    27.
    发明申请
    COVER PLATE FOR A COMPONENT OF A GAS TURBINE ENGINE 审中-公开
    气体涡轮发动机组件盖板

    公开(公告)号：US20160369632A1

    公开(公告)日：2016-12-22

    申请号：US15252874

    申请日：2016-08-31

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brandon W. Spangler ,  Russell J. Bergman

    IPC: F01D5/18 ,  F01D9/02 ,  F04D29/58 ,  F04D29/32 ,  F04D29/54 ,  F02C3/04 ,  F01D25/12

    Abstract: A component for a gas turbine engine includes a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.

    Abstract translation: 用于燃气涡轮发动机的部件包括具有非气体通道侧和气体通路侧的平台，从平台的气体路径侧延伸的翼型件和邻近该平台的非气体路径侧定位的盖板 平台。 盖板可以包括将冷却空气的第一部分连通到平台的第一冷却腔的第一多个开口以及可将冷却空气的第二部分连通到第二冷却腔的第二多个开口， 与第一个冷却腔分开。 第一冷却腔和第二冷却腔中的每一个可以包括多个增强特征。

    TOLERANCE RESISTANCE COVERPLATES
    29.
    发明申请
    TOLERANCE RESISTANCE COVERPLATES 有权
    耐受性覆盖

    公开(公告)号：US20160265372A1

    公开(公告)日：2016-09-15

    申请号：US14641470

    申请日：2015-03-09

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Ky H. Vu ,  Jeffrey J. DeGray ,  Ryan Alan Waite ,  Gina Cavallo ,  Thomas P. Dziuba

    IPC: F01D9/04 ,  F01D5/02 ,  F04D29/32 ,  F01D25/12

    CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/186 ,  F01D5/189 ,  F01D9/065 ,  F01D25/12 ,  F04D29/321 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/642 ,  F05D2240/126 ,  F05D2240/80 ,  F05D2260/20 ,  F05D2260/30 ,  Y02T50/676

    Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.

    Abstract translation: 燃气涡轮发动机部件组件包括相对于发动机中心轴线与第一部件周向间隔开的第一部件和第二部件。 第一挡板与第一部件相关联。 第二挡板与第二部件相关联。 第一和第二挡板中的每一个包括至少一个径向挡板。 在第一和第二挡板之间形成间隙以限定冷却空气入口。 第一盖板与第一挡板相关联以覆盖间隙的第一部分。 第二盖板与第二挡板相关联以覆盖间隙的第二部分。 第一和第二盖板彼此分开，并且包括至少一个盖板径向突片，其与相关联的至少一个挡板径向突片配合，以防止第一和第二挡板与第一和第二盖板之间的泄漏间隙。

    TURBINE BLADE HAVING FILM COOLING HOLE ARRANGEMENT
    30.
    发明申请
    TURBINE BLADE HAVING FILM COOLING HOLE ARRANGEMENT 审中-公开
    涡轮叶片有薄膜冷却孔安排

    公开(公告)号：US20160201473A1

    公开(公告)日：2016-07-14

    申请号：US14929692

    申请日：2015-11-02

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Laurie L. Burstynski

    IPC: F01D5/18 ,  F02C7/18 ,  F02C3/04

    CPC classification number: F01D5/186 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/3212 ,  F05D2240/81 ,  F05D2250/74 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes arranged in substantial conformance with the Cartesian coordinates set forth in Table 1 herein. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).

    Abstract translation: 涡轮叶片包括具有由两个平台周向侧连接的平台前缘和后缘的平台。 机翼从平台径向向外延伸到自由尖端。 翼型件包括通过相对的压力和吸力侧连接的翼型件前缘和后缘。 根从平台向内径向延伸。 平台和翼型件包括基本上符合本文表1所示的笛卡尔坐标的薄膜冷却孔。 相对于零坐标，笛卡尔坐标由轴向坐标，圆周坐标和径向坐标提供，并且冷却孔相对于0.200英寸（5.0mm）的指定坐标具有径向表面公差。

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