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    VANE ASSEMBLIES FOR GAS TURBINE ENGINES
    1.
    发明申请
    VANE ASSEMBLIES FOR GAS TURBINE ENGINES 有权
    用于气体涡轮发动机的VANE组件

    公开(公告)号：US20130205800A1

    公开(公告)日：2013-08-15

    申请号：US13358889

    申请日：2012-02-10

    申请人： Richard Ivakitch ,  Andreas Eleftheriou ,  David Denis ,  David Menheere

    发明人： Richard Ivakitch ,  Andreas Eleftheriou ,  David Denis ,  David Menheere

    IPC分类号： F01D9/02 ,  F01D11/00 ,  B23P17/00 ,  F02C3/04

    CPC分类号： F01D11/005 ,  F01D9/042 ,  F05D2240/55 ,  Y10T29/49245

    摘要： Vane assemblies for gas turbine engines and methods for assembling vane assemblies are disclosed. The vane assemblies may include at least one shroud having at least one vane-receiving portion, at least one vane having at least one end portion received in the vane-receiving portion, and at least one sealing member having an uncompressed cross-section that is substantially circular. The sealing member(s) are disposed between and in contact with the end portion of the vane and the vane-receiving portion of the shroud.

    摘要翻译： 公开了用于燃气涡轮发动机的叶片组件和组装叶片组件的方法。 叶片组件可以包括至少一个护罩，其具有至少一个叶片接收部分，至少一个叶片，其具有容纳在叶片容纳部分中的至少一个端部，以及至少一个具有未压缩横截面的密封构件， 大致圆形。 密封构件设置在叶片的端部和护罩的叶片接收部分之间并与之接触。

    Casing for an aircraft turbofan bypass engine
    3.
    发明授权
    Casing for an aircraft turbofan bypass engine 有权
    套装飞机涡扇风机旁路引擎

    公开(公告)号：US08979484B2

    公开(公告)日：2015-03-17

    申请号：US13344057

    申请日：2012-01-05

    申请人： Andreas Eleftheriou ,  David Menheere ,  David Denis

    发明人： Andreas Eleftheriou ,  David Menheere ,  David Denis

    IPC分类号： F01D25/24 ,  F01D9/06

    CPC分类号： F01D9/065 ,  F01D25/162 ,  F01D25/24 ,  F05D2230/232 ,  F05D2230/237

    摘要： A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.

    摘要翻译： 用于飞行器涡扇风扇旁路发动机的壳体包括外环，内毂和在它们之间径向延伸的多个支柱。 具有外壁和内壁的发动机芯壳的环形部分设置在外环和内毂之间，形成支撑上游分流器顶端结构的环形分流器。 环形分离器还包括设置在固定到外壁和支柱的环形分配器中的中间壁，以将负载从环形分配箱分配到支柱。

    Axial retention for fasteners in fan joint
    5.
    发明授权
    Axial retention for fasteners in fan joint 有权
    风扇接头紧固件的轴向保持

    公开(公告)号：US08967978B2

    公开(公告)日：2015-03-03

    申请号：US13558875

    申请日：2012-07-26

    申请人： David Denis ,  Richard Ivakitch

    发明人： David Denis ,  Richard Ivakitch

    IPC分类号： F01D5/02 ,  F01D5/00 ,  F01D5/30 ,  F02C7/36 ,  F02C7/20

    CPC分类号： F01D5/025 ,  F02K3/06 ,  F05D2220/36 ,  Y10T29/49234 ,  Y10T29/49321

    摘要： In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor. A standard retaining ring is attached to the joint to cover a portion of an enlarged head of each of the respective fasteners in order to prevent removal of the respective fasteners from the mounting openings in the joint before the respective fasteners are connected to the fan rotor.

    摘要翻译： 在燃气涡轮发动机中，风扇转子和压缩机转子连接到附接到轴的接头。 风扇转子通过多个紧固件连接到接头，多个紧固件延伸穿过接头中的安装开口并且通过风扇转子中的孔。 标准保持环附接到接头以覆盖每个相应紧固件的扩大头部的一部分，以便在相应的紧固件连接到风扇转子之前防止相应的紧固件从接头中的安装开口移除。

    Fan case abradable
    8.
    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

    申请人： Barry Barnett ,  David Denis ,  Andreas Eleftheriou

    发明人： Barry Barnett ,  David Denis ,  Andreas Eleftheriou

    IPC分类号： F01D21/00

    CPC分类号： F01D11/122 ,  F02K3/06

    摘要： 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.

    摘要翻译： 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。