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    Percussion drilled shaped through hole and method of forming
    3.
    发明授权
    Percussion drilled shaped through hole and method of forming 有权
    打孔器穿孔成型，成型方法

    公开(公告)号：US07820267B2

    公开(公告)日：2010-10-26

    申请号：US11841261

    申请日：2007-08-20

    申请人： Marc Fahndrich

    发明人： Marc Fahndrich

    IPC分类号： B32B3/24 ,  B23K26/38

    CPC分类号： F01D5/186 ,  B23K26/384 ,  B23K26/389 ,  B23K2101/001 ,  F05D2250/24 ,  F05D2250/241 ,  F05D2250/26 ,  F05D2250/27 ,  Y02T50/676 ,  Y10T428/24273

    摘要： A percussion drilled shaped through hole formed between a first surface and a second surface of a component and a method of forming the through hole. The through hole is defined by a primary crater, a secondary crater, and a metering hole. The primary crater is formed using laser percussion drilling in the first surface of the component. The secondary crater is formed using laser percussion drilling within the primary crater and substantially offset from a centerline of the primary crater. The metering hole is formed using laser percussion drilling within the secondary crater and extending through the component to the second surface. The primary crater, the secondary crater, and the metering hole define a Coand{hacek over (a)} ramp and provide for the flow of fluid through the percussion drilled shaped through hole according to the Coand{hacek over (a)} effect.

    摘要翻译： 在部件的第一表面和第二表面之间形成的通孔形成的打击乐器和形成通孔的方法。 通孔由主火山口，二次火山口和计量孔限定。 主要的火山口是在组件的第一个表面上使用激光打击钻探形成的。 二次火山口使用激光打击钻孔在主火山口内形成并且基本上偏离主火山口的中心线。 计量孔使用激光冲击钻在二次火山口内形成并延伸穿过该部件到第二表面。 主要火山口，二次火山口和计量孔定义了一个Coand（hacek over（a））斜坡，并根据Coand {hacek over（a）}效应为流体穿过冲击钻孔形孔提供流体。

    Ring sector of turbomachine turbine
    5.
    发明授权
    Ring sector of turbomachine turbine 有权
    涡轮机轮环

    公开(公告)号：US08684665B2

    公开(公告)日：2014-04-01

    申请号：US13018789

    申请日：2011-02-01

    申请人： Jean-Luc Bacha ,  Emmanuel Berche ,  Didier Jeannel

    发明人： Jean-Luc Bacha ,  Emmanuel Berche ,  Didier Jeannel

    IPC分类号： F01D5/14

    CPC分类号： F01D11/24 ,  F05D2240/11 ,  F05D2250/14 ,  F05D2250/16 ,  F05D2250/24 ,  F05D2250/26 ,  F05D2260/201 ,  Y02T50/676

    摘要： A turbine ring sector comprising a wall presenting an inside face and an outside face, in which the inside face defines an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage is disclosed. The multiply-perforated metal sheet has a bottom, and the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap. The variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value and then increases from the minimum value to a second maximum value.

    摘要翻译： 一种涡轮机环形部分，包括呈现内表面和外表面的壁，其中所述内侧面限定气体流过的轴向取向的气流通道; 并且公开了位于与气流通道相对的壁的侧面上的多孔金属片。 多孔金属片具有底部，壁的外表面和多孔金属片的底部之间的空间限定了间隙。 在其整个轴向范围上的间隙值的变化从第一最大值朝向最小值减小，然后从最小值增加到第二最大值。

    Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine
    6.
    发明授权
    Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine 有权
    用于混合在旁路喷气发动机中彼此初始分离引导的两股流体流的装置

    公开(公告)号：US07299635B2

    公开(公告)日：2007-11-27

    申请号：US10489599

    申请日：2002-08-29

    申请人： Karl Katheder

    发明人： Karl Katheder

    IPC分类号： F02K1/00

    CPC分类号： F02K1/40 ,  F05D2250/24 ,  F05D2250/712 ,  F05D2260/96 ,  Y02T50/671

    摘要： The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being provided, along the outer shaped lateral surface of which a cold bypass flow flows. The mixing tube is designed in the form of a truncated cone narrowing in the direction of flow and has openings arranged at the downstream end in the circumferential direction of the mixing-tube lateral surface in a cross-sectional plane lying perpendicularly to the longitudinal axis of the mixing tube. The hot core stream flowing through the mixing tube penetrates through the openings into the cold bypass flow flowing around the mixing-tube lateral surface. The openings have passage areas of elliptical shape with a major axis and a minor axis, the major axis of the passage areas running on the lateral surface of the mixing tube in the direction of flow of the fluids and the minor axis running perpendicularly thereto.

    摘要翻译： 本发明涉及一种用于混合两个流体流的装置，它们在双回路反应发动机中彼此独立地相互引导，一个混合管围绕设置的热核心流沿其外侧表面冷却旁路 流量流。 混合管被设计成在流动方向上变窄的截头锥体的形式，并且在垂直于纵向轴线的横截面中具有布置在混合管侧表面的圆周方向上的下游端的开口 混合管。 流经混合管的热芯流穿过开口进入流过混合管侧表面的冷旁路。 这些开口具有椭圆形的通道区域，具有长轴和短轴，通道区域的长轴在混合管的侧表面上沿流体的方向流动，而短轴垂直于其移动。

    Support structure for steam turbine bearing housing
    8.
    发明申请
    Support structure for steam turbine bearing housing 失效
    汽轮机轴承座支撑结构

    公开(公告)号：US20040156720A1

    公开(公告)日：2004-08-12

    申请号：US10360230

    申请日：2003-02-06

    发明人： Norman D. Lathrop ,  Douglas C. Hofer ,  Edward J. Sharrow ,  John Keeling ,  Robert J. Sherwood ,  Christen A. Vitrone

    IPC分类号： F01D025/26

    CPC分类号： F01D25/26 ,  F05D2250/24

    摘要： A casing (12) for a steam turbine section has a housing (14) installed therein for a bearing supporting a rotor for buckets. A housing support structure (10) includes a pair of horizontally extending struts (T1-T2) extending from a side (18) of the casing to the housing and a second pair of struts (T3, not shown) extending from the opposite side of the casing to the housing. The struts are in fluid communication with the interior of the housing and the atmosphere and both support the housing within the casing and vent the interior of the housing. Vertical struts (T4-T6) also extend between the casing and the housing. A foundation plate (20) is installed beneath the casing, and a pair of gibs (28) are installed on opposite sides of the casing along the longitudinal centerline thereof to strengthen the casing and prevent tilting of components within the casing when a vacuum within the casing is present.

    摘要翻译： 用于汽轮机部分的壳体（12）具有安装在其中的壳体（14），用于支撑用于铲斗的转子的轴承。 壳体支撑结构（10）包括从壳体的侧面（18）延伸到壳体的一对水平延伸的支柱（T1-T2），以及从壳体的相对侧延伸的第二对支柱（T3，未示出） 外壳到外壳。 支柱与壳体和大气的内部流体连通，并且两者都支撑壳体内的壳体并且排出壳体的内部。 垂直支柱（T4-T6）也在外壳和外壳之间延伸。 底板（20）安装在壳体下方，一对臂（28）沿其纵向中心线安装在壳体的相对侧上，以加强壳体并防止壳体内的部件倾斜 套管存在。

    NACELLE AND COMPRESSOR INLET ARRANGEMENTS
    10.
    发明申请
    NACELLE AND COMPRESSOR INLET ARRANGEMENTS 审中-公开
    NACELLE和压缩机入口安排

    公开(公告)号：US20160076460A1

    公开(公告)日：2016-03-17

    申请号：US14824292

    申请日：2015-08-12

    申请人： United Technologies Corporation

    发明人： Frederick M. Schwarz ,  Robert E. Malecki

    IPC分类号： F02C9/18 ,  F02C3/04 ,  F02C7/36 ,  F01D25/24

    CPC分类号： F02C9/18 ,  B64D2033/022 ,  F01D25/24 ,  F02C3/04 ,  F02C7/05 ,  F02C7/36 ,  F02K3/06 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/24

    摘要： A gas turbine engine includes a nacelle defining a centerline axis and an annular splitter radially inward from the nacelle. A spinner is radially inward of the nacelle forward of a compressor section. A fan blade extends from a fan blade platform. A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H is the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio of X/H≧1.5 for reducing foreign object debris (FOD) intake into the compressor section.

    摘要翻译： 燃气涡轮发动机包括限定中心线轴线的机舱和从机舱径向向内的环形分配器。 旋转器在压缩机部分的前方的机舱的径向内侧。 风扇叶片从风扇叶片平台延伸。 距离X是从第一点到第二点的轴向距离，其中第一点被限定在环形分配器的前缘上，第二点限定在风扇叶片的前缘上，其中风扇叶片与 风扇叶片平台。 距离H是从第一点到第二点的径向距离。 第一点和第二点的相对位置由减少异物（FOD）进入压缩机段的X /H≥1.5的比率决定。