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    GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE
    3.
    发明申请
    GAS TURBINE ENGINE TURBINE VANE AIRFOIL PROFILE 有权
    气体涡轮发动机涡轮风扇气翼剖面

    公开(公告)号：US20140000287A1

    公开(公告)日：2014-01-02

    申请号：US13539917

    申请日：2012-07-02

    申请人： Brandon W. Spangler ,  Russell J. Bergman

    发明人： Brandon W. Spangler ,  Russell J. Bergman

    IPC分类号： F01D25/12

    CPC分类号： F01D25/12 ,  F01D9/02 ,  F01D9/041 ,  F05D2240/81 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The inner and outer platforms respectively include inner and outer sets of film cooling holes, wherein one of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).

    摘要翻译： 用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。 翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 内部和外部平台分别包括内部和外部薄膜冷却孔组，其中内部和外部薄膜冷却孔组中的一个基本上与基于以下的笛卡尔坐标系中的一组所描述的平台冷却孔位置形成： 表1和2.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。 表1和表2中笛卡尔坐标的冷却孔相对于0.200英寸（5.08毫米）的指定坐标具有直径表面公差。

    HYBRID INNER AIR SEAL FOR GAS TURBINE ENGINES
    7.
    发明申请
    HYBRID INNER AIR SEAL FOR GAS TURBINE ENGINES 有权
    用于气体涡轮发动机的混合内部空气密封

    公开(公告)号：US20130183145A1

    公开(公告)日：2013-07-18

    申请号：US13351290

    申请日：2012-01-17

    申请人： Joseph T. Caprario ,  Russell J. Bergman ,  Pamela A. Humphrey ,  Jonathan Perry Sandoval

    发明人： Joseph T. Caprario ,  Russell J. Bergman ,  Pamela A. Humphrey ,  Jonathan Perry Sandoval

    IPC分类号： F01D11/00

    CPC分类号： F01D11/001 ,  F01D9/04 ,  F01D11/025

    摘要： A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.

    摘要翻译： 涡轮部分具有承载涡轮叶片的涡轮转子。 涡轮机叶片包括在径向内部位置处的密封构件。 叶片部分由多个周向间隔开的叶片部件形成，每个叶片部件具有从平台径向向外延伸的翼型件。 第一密封构件固定到平台上，并且被定位成与相对于第一密封构件沿一个轴向方向定位的叶片相邻的密封件。 第二密封构件周向地延伸超过至少多个叶片部件，并且定位成在与第一叶片相对的轴向侧上与叶片的密封构件相邻。 还公开并要求保护叶片部件。

    COVER PLATE FOR TURBINE VANE ASSEMBLY
    8.
    发明申请
    COVER PLATE FOR TURBINE VANE ASSEMBLY 有权
    涡轮风扇组件盖板

    公开(公告)号：US20110229305A1

    公开(公告)日：2011-09-22

    申请号：US12726021

    申请日：2010-03-17

    申请人： Russell J. Bergman ,  Joseph W. Bridges ,  Kevin R. Richter

    发明人： Russell J. Bergman ,  Joseph W. Bridges ,  Kevin R. Richter

    IPC分类号： F01D25/12 ,  F01D9/00 ,  B32B3/10

    CPC分类号： F01D9/041 ,  F01D25/12 ,  F05D2260/201 ,  Y02T50/676 ,  Y10T428/24273 ,  Y10T428/24802

    摘要： Embodiments of a cover plate and material blank for forming the cover plate may include features and characteristics to accommodate tolerance issues in a turbine vane assembly. In one embodiment, the cover plate is formed from a material blank configured to provide the cover plate with a flexible flange area that can be secured to the turbine vane assembly. The flange area may have a range of motion that may be responsive to an installation force, which effectively modifies the configuration of the cover plate to such degree as to seal the cover plate to the turbine vane assembly.

    摘要翻译： 用于形成盖板的盖板和材料坯料的实施例可以包括用于适应涡轮叶片组件中的公差问题的特征和特征。 在一个实施例中，盖板由材料坯料形成，其被配置为向盖板提供可固定到涡轮叶片组件的柔性凸缘区域。 凸缘区域可以具有可以响应于安装力的运动范围，该安装力有效地将盖板的构造改变为将盖板密封到涡轮叶片组件的程度。

    Cover plate for a component of a gas turbine engine
    9.
    发明授权
    Cover plate for a component of a gas turbine engine 有权
    用于燃气涡轮发动机的部件的盖板

    公开(公告)号：US09500099B2

    公开(公告)日：2016-11-22

    申请号：US13539806

    申请日：2012-07-02

    申请人： Brandon W. Spangler ,  Russell J. Bergman

    发明人： Brandon W. Spangler ,  Russell J. Bergman

    IPC分类号： F01D25/12 ,  F01D5/18

    CPC分类号： F01D5/18 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F02C3/04 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/11 ,  F05D2260/201 ,  F05D2260/22141

    摘要： A component for a gas turbine engine according to an exemplary embodiment of the present disclosure includes, among other possible things, 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.

    摘要翻译： 根据本公开的示例性实施例的用于燃气涡轮发动机的部件除了其它可能的内容之外还包括具有非气体通路侧和气体通路侧的平台，从平台的气体路径侧延伸的翼型， 以及邻近所述平台的非气体路径侧定位的盖板。 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。

    AIRFOIL COOLING ARRANGEMENT
    10.
    发明申请
    AIRFOIL COOLING ARRANGEMENT 有权
    AIRFOIL冷却布置

    公开(公告)号：US20140010632A1

    公开(公告)日：2014-01-09

    申请号：US13539838

    申请日：2012-07-02

    申请人： Brandon W. Spangler ,  Russell J. Bergman

    发明人： Brandon W. Spangler ,  Russell J. Bergman

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F01D9/065 ,  Y02T50/676

    摘要： An airfoil according to an exemplary embodiment of the present disclosure can include an airfoil body having a plurality of film cooling holes that extend through an exterior surface of the airfoil body. Each of the plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the airfoil.

    摘要翻译： 根据本公开的示例性实施例的翼型件可以包括具有延伸穿过翼型件主体的外表面的多个膜冷却孔的翼型件主体。 多个膜冷却孔中的每一个根据如表1所示的X，Y和Z的笛卡尔坐标值以几何坐标突破外表面。每个几何坐标是从前缘上的参考点 机翼平台的轨道。