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105 条记录 (耗时 0.013 秒)

    TRIEBWERKS-EINLAUFKLAPPE ZUR ANBRINGUNG AN DEM GEHÄUSE EINES LUFTEINLASSES EINES FLUGZEUG-TRIEBWERKS SOWIE TRIEBWERK MIT EINER SOLCHEN TRIEBWERKS-EINLAUFKLAPPE UND FLUGZEUGSYSTEM
    63.
    发明授权
    TRIEBWERKS-EINLAUFKLAPPE ZUR ANBRINGUNG AN DEM GEHÄUSE EINES LUFTEINLASSES EINES FLUGZEUG-TRIEBWERKS SOWIE TRIEBWERK MIT EINER SOLCHEN TRIEBWERKS-EINLAUFKLAPPE UND FLUGZEUGSYSTEM 有权
    发动机进气口FLAP用于连接到飞机发动机和发动机这样的发动机吸气瓣和飞机系统的外壳进气口

    公开(公告)号：EP2254795B1

    公开(公告)日：2011-10-26

    申请号：EP09708711.8

    申请日：2009-02-04

    申请人： Airbus Operations GmbH

    发明人： BOLENDER, Lars ,  WAGNON, Sébastien

    IPC分类号： B64D33/02 ,  B64D15/16

    CPC分类号： B64D15/16 ,  B64D33/02 ,  B64D2033/0213 ,  B64D2033/0233 ,  F02C7/047 ,  F02C7/055 ,  Y02T50/672

    摘要： Engine inlet flap (K) for mounting on the housing of an air inlet or air inlet duct of an engine of an aircraft, having a first end (E1) and a second end (E2) arranged in opposition thereto at a distance therefrom in the longitudinal direction (L) of the inlet flap, wherein the longitudinal direction (L) in the given installation is aligned against the flow direction (S) of the air flowing into the engine. The inlet flap (K) comprises an inlet flap base body (1) with a connector device for a jointed connector for jointed connection of the inlet flap base body (1) to the housing of the air inlet or air inlet duct, with a rotational axis (A) running along the second end (E2), an inlet flap extension piece (2) structurally integrated with the inlet flap base body (1), with a first and a second lateral piece (5, 6), which extends from the inlet flap base body (1) on the two opposed lateral edges (5, 6) of the inlet flap (K) running in the longitudinal direction (L) with a number of transverse struts (11) or longitudinal struts, arranged in the leading region of the engine inlet flap (K).

    SCHALLDÄMPFER FÜR EIN HILFSTRIEBWERK EINES FLUGZEUGS
    65.
    发明公开
    SCHALLDÄMPFER FÜR EIN HILFSTRIEBWERK EINES FLUGZEUGS 有权
    消声器飞机的一台备用发动机

    公开(公告)号：EP2334558A2

    公开(公告)日：2011-06-22

    申请号：EP09736200.8

    申请日：2009-10-09

    申请人： Airbus Operations GmbH

    发明人： STAROBINSKI, Rudolf ,  SIERCKE, Matthias

    IPC分类号： B64D33/04 ,  B64D41/00

    CPC分类号： B64D41/00 ,  B64D33/06 ,  B64D2033/0213 ,  B64D2041/002 ,  F02C7/24 ,  F02C7/32 ,  F02K1/827 ,  F05D2220/50 ,  Y02T50/44

    摘要： The invention relates to a sound absorber (2) for an auxiliary engine of an aircraft comprising an inlet (46), an outlet (48), a housing (4), and a flow channel (6) which has a porous wall material and is arranged in the housing (4). An intermediate space is formed between the housing (4) and the flow channel (6). Said intermediate space is divided into outer cells (10-26) arranged around the flow channel (6) by way of one or more partitions (8). Thus, a very compact sound absorber having very good sound insulation is made possible. By dividing the outer cells (10-26) into outer areas and inner areas, adapting the shape of the sound absorber (2) to a rear section of the aircraft, and attaching a ring-shaped channel to the outlet (48), the sound insulation can be improved further.

    Auxiliary power unit intake duct with aero-acoustic guide vanes
    66.
    发明公开
    Auxiliary power unit intake duct with aero-acoustic guide vanes 有权
    与空气声学引导入口管叶片用于辅助动力单元

    公开(公告)号：EP1749993A3

    公开(公告)日：2011-01-05

    申请号：EP05078054.3

    申请日：2005-12-28

    申请人： Airbus Operations S.L.

    发明人： Hernanz Manrique, José Angel ,  Kruse, Jürgen Heinrich

    IPC分类号： F02C7/045 ,  B64D33/02 ,  F02C7/04

    CPC分类号： B64D41/00 ,  B64D2033/0213 ,  F02C7/04 ,  F02C7/32

    摘要： An auxiliary power unit intake duct for an aircraft, comprising
    an internal straight portion 1a, an internal first bend portion 1b and an internal second bend portion 1c, extending between an air inlet 2 and a plenum entry 3 of the auxiliary power unit,
    a plurality of acoustic guides vanes 4,5 located in the straight portion la of the intake duct 1, extending horizontally between opposite side portions of the straight portion 1a; and
    a plurality of curved aerodynamic guide vanes 6,7 located in the second bend portion 1c proximate to said plenum inlet 3, extending vertically between a top portion and a bottom portion of the second bend portion 1c, each of the curved aerodynamic guide vanes 6,7 being concentric with said bend curvature of the second bend portion 1c.

    Exhaust eductor system with a recirculation baffle
    67.
    发明公开
    Exhaust eductor system with a recirculation baffle 审中-公开
    带有再循环挡板的排气喷射系统

    公开(公告)号：EP1918202A2

    公开(公告)日：2008-05-07

    申请号：EP07119681.0

    申请日：2007-10-30

    申请人： Honeywell International Inc.

    发明人： Judd, Z. Daniel

    IPC分类号： B64D33/04 ,  B64D41/00

    CPC分类号： B64D33/04 ,  B64D41/00 ,  B64D2033/0213

    摘要： An exhaust eductor system (110) includes a primary exhaust nozzle (112) configured to transport an active flow stream (120); and a mixing duct (114) at least partially surrounding the primary exhaust nozzle (112) and configured to transport a passive flow stream that is entrained by mixing with the active flow stream (120) from the primary exhaust nozzle (112). The mixing duct (114) has an interior, and a baffle (126) on the interior of the mixing duct (114) is configured to prevent the mixed flow streams from exiting the mixing duct (114).

    摘要翻译： 排气喷射器系统（110）包括构造成输送活性流动流（120）的主排气喷嘴（112）; 以及至少部分地围绕所述主排气喷嘴（112）并且构造成传输通过与所述主排气喷嘴（112）的所述活性流动流（120）混合而夹带的被动流动流的混合管道（114）。 混合管（114）具有内部，并且混合管（114）的内部上的挡板（126）被配置成防止混合的液流从混合管（114）排出。

    Pre-hung inlet door system
    68.
    发明公开
    Pre-hung inlet door system 有权
    Einlasstür

    公开(公告)号：EP1834872A1

    公开(公告)日：2007-09-19

    申请号：EP06111358.5

    申请日：2006-03-17

    申请人： Honeywell International Inc.

    发明人： Hein, Jeffrey ,  Williams, Nicholas

    IPC分类号： B64C1/14 ,  F02C7/04 ,  B64D41/00

    CPC分类号： F02C7/32 ,  B64D33/12 ,  B64D41/00 ,  B64D2033/0213 ,  B64D2041/002 ,  F02C6/08

    摘要： A pre-hung air inlet door assembly (40) comprises an inlet door (41), a door box frame (42), and an actuation system (43). The door box frame is fastened to the support structure of an aircraft. The inlet door is operationally connected to the actuation system. The entire pre-hung air inlet door assembly can be preassembled for quick installation into an aircraft. Pre-assembly eliminates trimming operations and rigging and misalignment issues. The pivot shafts (46,47) and bearing housings (44,45) of the pre-hung air inlet door assembly can be accessed from outside the aircraft when repairs and/or replacement components are needed.

    摘要翻译： 预悬空进气门组件（40）包括入口门（41），门框框架（42）和致动系统（43）。 门框框架固定在飞机的支撑结构上。 入口门可操作地连接到致动系统。 整个预悬挂进气门组件可以预先组装，以便快速安装到飞机上。 预组装消除了修整操作和索具和不对齐问题。 当需要维修和/或更换部件时，可以从飞机外部访问预悬空进气门组件的枢轴（46,47）和轴承座（44,45）。