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    Casing support structure
    3.
    发明授权
    Casing support structure 有权

    公开(公告)号：US09945261B2

    公开(公告)日：2018-04-17

    申请号：US14945784

    申请日：2015-11-19

    申请人： SNECMA

    发明人： Thierry Georges Paul Papin ,  Kaelig Merwen Orieux ,  Regis Eugene Henri Servant

    IPC分类号： F01D25/24 ,  F01D25/28 ,  F01D25/16

    CPC分类号： F01D25/28 ,  F01D25/162 ,  F01D25/24 ,  Y02T50/672

    摘要： A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.

    AIRCRAFT TURBOFAN COMPRISING AN INTERMEDIATE RING WITH SIMPLIFIED DOWNSTREAM SUPPORT
    4.
    发明申请
    AIRCRAFT TURBOFAN COMPRISING AN INTERMEDIATE RING WITH SIMPLIFIED DOWNSTREAM SUPPORT 有权
    包含简单的下游支撑的中间环的飞机涡轮机

    公开(公告)号：US20150159554A1

    公开(公告)日：2015-06-11

    申请号：US14272911

    申请日：2014-05-08

    申请人： SNECMA

    发明人： Fabrice Cretin ,  Yvan Guezel ,  Francois Marie Paul Marlin ,  Thierry Georges Paul Papin ,  Alain Marc Lucien Bromann ,  Damien Lourit

    IPC分类号： F02C7/04

    CPC分类号： F02C7/04 ,  F01D25/243 ,  F02K3/06 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2260/30 ,  F05D2260/31 ,  Y02T50/672 ,  Y10T137/0402 ,  Y10T137/0536

    摘要： This invention relates to an assembly (100) for an aircraft turbofan comprising a flowpath splitter (40) downstream from which there is firstly a fan flowpath (31) inner delimitation ring (44) and secondly a compressor case (42), the assembly comprising a plurality of outlet guide vanes (34) provided with an inner platform (50) located in the downstream continuity of the delimitation ring.According to the invention, the assembly comprises at least one part (52) to support the delimitation ring (44), comprising a radially outer end (52b) fixed to a downstream part of this ring (44) and a radially inner end (52a) fixed to the compressor case (42).

    摘要翻译： 本发明涉及一种用于飞行器涡扇风扇的组件（100），其包括在下游的流路分流器（40），其中首先具有风扇流路（31）内定界环（44），其次是压缩机壳体（42），该组件包括 多个出口导叶（34）设置有位于定界环的下游连续性的内平台（50）。 根据本发明，组件包括支撑定界环（44）的至少一个部分（52），包括固定到该环（44）的下游部分的径向外端（52b）和径向内端（52a） ）固定到压缩机壳体（42）。