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    AIR COOLING DESIGN FOR TAIL-CONE GENERATOR INSTALLATION
    21.
    发明申请
    AIR COOLING DESIGN FOR TAIL-CONE GENERATOR INSTALLATION 有权
    尾气发电机安装的空气冷却设计

    公开(公告)号：US20140079530A1

    公开(公告)日：2014-03-20

    申请号：US13616230

    申请日：2012-09-14

    Applicant: Gordon FERCH ,  Daniel ALECU ,  Xiaoliu LIU ,  Barry BARNETT ,  Dileepan SIVALINGAM ,  Carmine FORGIONE

    Inventor： Gordon FERCH ,  Daniel ALECU ,  Xiaoliu LIU ,  Barry BARNETT ,  Dileepan SIVALINGAM ,  Carmine FORGIONE

    IPC: F01D25/14

    CPC classification number: F01D15/10 ,  F02C7/12 ,  Y02T50/671 ,  Y02T50/675

    Abstract: A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an outlet of a support strut positioned in fluid communication with the tail-cone cavity. The fairing inlet and the strut outlet are both positioned in a plane substantially perpendicular to a longitudinal plane of the engine. In this manner, circulation of the bypass air through the fairing, the tail-cone cavity, and the strut may be achieved. The bypass air directed through the fairing further enables cooling of service lines accommodated in the fairing. A lobe mixer is further used to direct the fairing and shield the latter from core exhaust.

    Abstract translation: 一种用于冷却安装在发动机尾锥中的发电机的系统。 该系统包括整流罩，其通过入口从旁路管道接收空气，并将旁路空气引导到尾锥的空腔以冷却发电机。 然后，旁路空气通过与尾锥腔流体连通的支撑支柱的出口排出。 整流罩入口和支柱出口都位于基本上垂直于发动机的纵向平面的平面内。 以这种方式，可以实现旁路空气通过整流罩，尾锥腔和支柱的循环。 引导通过整流罩的旁路空气进一步使得容纳在整流罩中的服务线的冷却。 进一步使用叶片混合器来引导整流罩并将其从核心排气屏蔽起来。

    Labyrinth seal repair
    24.
    发明授权
    Labyrinth seal repair 有权
    迷宫密封维修

    公开(公告)号：US07726021B2

    公开(公告)日：2010-06-01

    申请号：US11528648

    申请日：2006-09-28

    Applicant: Barry Barnett

    Inventor： Barry Barnett

    IPC: B23P6/00 ,  F01D11/02

    CPC classification number: F01D11/02 ,  B23P6/005 ,  B23P11/025 ,  F05D2230/80 ,  Y10T29/49318 ,  Y10T29/49719 ,  Y10T29/4973

    Abstract: A method for repairing damaged fins in a labyrinth seal without the use of welding or metallurgical bonding by removing a section of the shaft containing the damaged fins, and providing a sleeve with replacement fins.

    Abstract translation: 一种用于在不使用焊接或冶金接合的情况下修复迷宫式密封件中的损坏的翅片的方法，通过移除包含损坏的翅片的轴的一部分，以及提供具有替换翅片的套筒。

    Fan case abradable
    25.
    发明申请
    Fan case abradable 审中-公开
    风箱磨损

    公开(公告)号：US20080063508A1

    公开(公告)日：2008-03-13

    申请号：US11517299

    申请日：2006-09-08

    Applicant: Barry Barnett ,  David Denis ,  Andreas Eleftheriou

    Inventor： Barry Barnett ,  David Denis ,  Andreas Eleftheriou

    IPC: F01D21/00

    CPC classification number: F01D11/122 ,  F02K3/06

    Abstract: A fan case and method of manufacturing a fan case, for a gas turbine engine, where the fan case has a hollow tubular metal shell with: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, and the shell wall includes an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet.

    Abstract translation: 一种用于燃气涡轮发动机的风扇壳体和风扇壳体的制造方法，其中所述风扇壳体具有中空管状金属壳体，所述中空管状金属壳体具有中心对称轴线; 一个入口 一个出口 围绕所述轴线的周壁围绕多个旋转风扇叶片的顶端，并且所述壳壁包括限定环形可磨损材料凹部的上游部分，所述环形可磨损材料凹部轴向延伸，具有在所述壳入口处的上游端和位于所述壳体入口上游的下游端 外壳出口。

    Vane assembly with grommet
    26.
    发明申请
    Vane assembly with grommet 有权
    叶轮组件与索环

    公开(公告)号：US20070237633A1

    公开(公告)日：2007-10-11

    申请号：US11223148

    申请日：2005-09-12

    Applicant: Barry Barnett

    Inventor： Barry Barnett

    IPC: F01D9/00

    CPC classification number: F01D9/042 ,  F02C7/05 ,  F05D2260/30

    Abstract: A vane assembly for a gas turbine engine including a shroud ring with openings and isolating means isolating a vane extremity within each opening, the isolating means cooperating to form a continuous gas path surface completely covering at least an axial portion of a surface of the shroud ring.

    Abstract translation: 一种用于燃气涡轮发动机的叶片组件，其包括具有开口的护罩环和隔离每个开口内的叶片末端的隔离装置，该隔离装置配合以形成完全覆盖护罩环表面的至少一个轴向部分的连续气体路径表面 。

    Foreign object damage resistant vane assembly
    27.
    发明申请
    Foreign object damage resistant vane assembly 有权
    异物损坏叶片组件

    公开(公告)号：US20070237632A1

    公开(公告)日：2007-10-11

    申请号：US11223129

    申请日：2005-09-12

    Applicant: Barry Barnett ,  Bruce Fielding

    Inventor： Barry Barnett ,  Bruce Fielding

    IPC: F01D9/00

    CPC classification number: F01D9/042 ,  F02C7/05 ,  F05D2260/30

    Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined therein about a circumference thereof and vanes extending radially from the shroud with a vane tip in each opening. Isolating means are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining means for restricting movement of the vane tip in an axial direction relative to said shroud.

    Abstract translation: 一种用于燃气涡轮发动机的叶片组件，其包括围绕其周围限定的开口的护罩和在每个开口中具有叶片从护罩径向延伸的叶片。 隔离装置设置在每个开口中以将叶片尖端与护罩环隔离。 每个叶片尖端通过用于限制叶片尖端在相对于所述护罩的轴向上的运动的保持装置与护罩接合。

    VANE ASSEMBLY WITH OUTER GROMMETS
    28.
    发明申请
    VANE ASSEMBLY WITH OUTER GROMMETS 有权
    VANE组装与外部GROMMETS

    公开(公告)号：US20070098557A1

    公开(公告)日：2007-05-03

    申请号：US11467406

    申请日：2006-08-25

    Applicant: Barry Barnett ,  David Denis

    Inventor： Barry Barnett ,  David Denis

    IPC: F01D11/00

    CPC classification number: F01D9/042 ,  F02C7/05 ,  F05D2250/70 ,  F05D2260/30 ,  F05D2300/222 ,  F05D2300/43 ,  F05D2300/431

    Abstract: A compressor vane having a root, a tip and an airfoil portion extending between the root and the tip is disclosed. A grommet is used in conjunction with the vane and has a lip sealingly surrounding a portion of the vane root and a circumferential portion protruding around a perimeter of the lip in engagement with a surface of a platform of the vane root. The circumferential portion has a profile similar to that of the airfoil portion.

    Abstract translation: 公开了一种具有根，尖端和在根部和尖端之间延伸的翼型部分的压缩机叶片。 索环与叶片一起使用，并且具有密封地围绕叶片根部的一部分的唇缘和围绕唇缘的周边突出地与叶根的平台的表面接合的周向部分。 圆周部分具有类似于翼型部分的轮廓。

    Coupling element for torque transmission in a gas turbine engine
    30.
    发明授权
    Coupling element for torque transmission in a gas turbine engine 有权
    用于燃气涡轮发动机中的扭矩传递的耦合元件

    公开(公告)号：US09297422B2

    公开(公告)日：2016-03-29

    申请号：US13660039

    申请日：2012-10-25

    Applicant: Barry Barnett ,  Phillipe Bonniere ,  Daniel Alecu

    Inventor： Barry Barnett ,  Phillipe Bonniere ,  Daniel Alecu

    IPC: F16D3/80 ,  F02C7/12 ,  F16D1/10 ,  F01D5/02

    CPC classification number: F16D1/101 ,  F01D5/026 ,  F05D2260/20 ,  F16D2001/103 ,  Y02T50/675 ,  Y10T403/25 ,  Y10T464/10

    Abstract: A gas turbine engine having a coupling element for coupling a first shaft to a second shaft, the second shaft being substantially axially aligned with the first shaft, the coupling element provided with an exterior surface that engages an opposing interior surface of the first shaft and an interior surface that engages an opposing exterior surface of the second shaft to facilitate torque transfer between the first shaft and the second shaft when rotated together, wherein the coupling element and at least one of the first and second shafts cooperate to define at least one fluid passageway therebetween.

    Abstract translation: 一种燃气涡轮发动机，其具有用于将第一轴联接到第二轴的联接元件，所述第二轴与所述第一轴基本上轴向对齐，所述联接元件设置有与所述第一轴的相对的内表面接合的外表面， 内表面，其接合所述第二轴的相对的外表面，以便当一起旋转时促进在所述第一轴和所述第二轴之间的扭矩传递，其中所述联接元件和所述第一和第二轴中的至少一个协作以限定至少一个流体通道 之间。

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