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    FIRE CONTAINMENT APPARATUSES FOR AIRCRAFT DUCT ASSEMBLIES
    2.
    发明公开
    FIRE CONTAINMENT APPARATUSES FOR AIRCRAFT DUCT ASSEMBLIES 审中-公开
    BRANDEINDÄMMUNGSVORRICHTUNGENFÜRFLUGZEUGLEITUNGSKANALBAUGRUPPEN

    公开(公告)号：EP3031733A1

    公开(公告)日：2016-06-15

    申请号：EP15197398.9

    申请日：2015-12-01

    申请人： Honeywell International Inc.

    发明人： WILCOX, David Eugene ,  KOLBERG, Thomas ,  HAMMER, Mike

    IPC分类号： B64D41/00 ,  F02C7/25

    CPC分类号： B64D33/02 ,  B64D41/00 ,  B64D2033/0213 ,  F02C7/25

    摘要： An intake duct assembly for an auxiliary power unit system is provided. A first inlet adapter (210) includes at least one hole (332) through the duct wall. A fire containment apparatus (230) forms a first passage to direct intake air between exterior wall of the aircraft and the enclosure. An inner duct (500) mounted on the first inlet adapter (210) at a first position downstream of the at least one hole and mounted on a second inlet adapter (220). An outer sheath (550) is mounted on the first inlet adapter (210) at a second position upstream of the at least one hole and mounted on the second inlet adapter (220). The outer sheath (550) circumscribes the inner duct (500) to form at least a portion of a barrier annulus between the inner duct (500) and outer sheath (550) in fluid communication with the first passage via the at least one hole in the first inlet adapter (210).

    摘要翻译： 提供了一种用于辅助动力单元系统的进气管组件。 第一入口适配器（210）包括穿过管道壁的至少一个孔（332）。 防火装置（230）形成第一通道以引导飞行器的外壁和外壳之间的进气。 安装在所述第一入口适配器（210）上的内部管道（500）处于所述至少一个孔的下游的第一位置并安装在第二入口适配器（220）上。 外护套（550）在所述第一入口适配器（210）的第二位置处安装在所述至少一个孔的上游，并且安装在所述第二入口适配器（220）上。 外护套（550）围绕内管道（500）以形成内管道（500）和外护套（550）之间的阻挡环的至少一部分，其通过至少一个孔与第一通道流体连通 第一入口适配器（210）。

    AUXILIARY POWER AND THRUST UNIT DRIVE SYSTEM AND METHOD OF OPERATION
    3.
    发明公开
    AUXILIARY POWER AND THRUST UNIT DRIVE SYSTEM AND METHOD OF OPERATION 审中-公开
    HILFSANTRIEBSSYSTEM SOWIE VERFAHREN ZUM BETRIEB

    公开(公告)号：EP2998543A1

    公开(公告)日：2016-03-23

    申请号：EP15185670.5

    申请日：2015-09-17

    申请人： The Boeing Company

    发明人： AHMAD, Parvez N. ,  ELLIS, David

    IPC分类号： F02C7/32 ,  B64D41/00 ,  F02C7/36

    CPC分类号： B64D41/00 ,  B64D2033/0213 ,  F01D5/02 ,  F01D5/12 ,  F01D9/02 ,  F01D15/12 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/50 ,  F05D2240/12 ,  F05D2240/24

    摘要： An aircraft auxiliary power and thrust unit includes at least one blade mounted to a fan shaft which are mounted to a tail cone of the aircraft and rotatable relative to the tail cone. Also included is an air intake assembly which includes an opening defined by the tail cone and a channel in fluid communication with the opening and the at least one blade. A first drive shaft positioned to extend in a direction transverse to the fan shaft and engagageable to rotate with the fan shaft and first drive shaft engaged and the first drive shaft engagageable to a second drive shaft positioned transverse to the first drive shaft such that the second drive shaft rotates with the first drive shaft with the first and second drive shafts engaged. The second drive shaft is positioned outside of the channel of the air intake.

    摘要翻译： 飞机辅助动力和推力单元包括安装到风扇轴的至少一个叶片，其安装到飞行器的尾锥并相对于尾锥可旋转。 还包括进气组件，其包括由尾锥限定的开口和与开口和至少一个叶片流体连通的通道。 第一驱动轴，其定位成沿横向于所述风扇轴的方向延伸并且能够与所述风扇轴和所述第一驱动轴接合并且所述第一驱动轴可接合于横向于所述第一驱动轴定位的第二驱动轴旋转， 驱动轴随着第一和第二驱动轴接合而与第一驱动轴一起旋转。 第二驱动轴位于进气口通道的外侧。

    AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM AIR DUCT ARRANGEMENT
    4.
    发明公开
    AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM AIR DUCT ARRANGEMENT 有权
    LUFTKANALANORDNUNGFÜRFLUGZEUGKLIMAREGELUNGSSYSTEM

    公开(公告)号：EP2998225A1

    公开(公告)日：2016-03-23

    申请号：EP15181584.2

    申请日：2015-08-19

    申请人： Rolls-Royce plc

    发明人： Stieger, Rory D ,  Raffaelli, Lorenzo

    IPC分类号： B64D13/06 ,  B64C21/06 ,  B64D33/02

    CPC分类号： B64D13/08 ,  B64C21/06 ,  B64D13/06 ,  B64D2013/0603 ,  B64D2013/0611 ,  B64D2013/0622 ,  B64D2033/0213 ,  Y02T50/166 ,  Y02T50/56

    摘要： An air duct arrangement (58) for an aircraft (40). The arrangement (58) comprises an environmental control system (ECS) (50). The ECS (50) comprises an air inlet (60) arranged to ingest a low velocity portion of a boundary layer flow adjacent the aircraft fuselage (44), and to deliver a flow of air to an environmental control system air intake (66). The arrangement (58) further comprises an ejector (70) arranged to receive an ECS exhaust (76), and boundary layer air from an aft region of the aircraft (40), and to exhaust air to the ambient airstream at an aft portion of the aircraft (40).

    摘要翻译： 一种用于飞行器（40）的风道装置（58）。 该装置（58）包括环境控制系统（ECS）（50）。 ECS（50）包括一个空气入口（60），它被配置成摄取邻近飞行器机身（44）的边界层流的低速部分，并将空气流传送到环境控制系统进气口（66）。 所述装置（58）还包括排出器（70），其被排列成接收ECS排气（76）和来自飞行器（40）的后部区域的边界层空气，并且在空气的后部将空气排出到周围的空气流 飞机（40）。

    TRIEBWERKS-EINLAUFKLAPPE ZUR ANBRINGUNG AN DEM GEHÄUSE EINES LUFTEINLASSES EINES FLUGZEUG-TRIEBWERKS SOWIE TRIEBWERK MIT EINER SOLCHEN TRIEBWERKS-EINLAUFKLAPPE UND FLUGZEUGSYSTEM
    9.
    发明公开
    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：EP2254795A1

    公开(公告)日：2010-12-01

    申请号：EP09708711.8

    申请日：2009-02-04

    申请人： Airbus Operations GmbH

    发明人： BOLENDER, Lars ,  WAGNON, Sébastian

    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).

    Auxiliary power unit inlet door position control system and method
    10.
    发明公开
    Auxiliary power unit inlet door position control system and method 有权
    系统和方法，用于控制辅助动力单元的进气阀的位置

    公开(公告)号：EP1767455A3

    公开(公告)日：2008-01-30

    申请号：EP06121311.2

    申请日：2006-09-27

    申请人： Honeywell International Inc.

    发明人： Riley, Harold J.

    IPC分类号： B64D33/02 ,  B64D41/00

    CPC分类号： B64D41/00 ,  B64D2033/0213 ,  B64D2041/002

    摘要： An auxiliary power unit (APU) (100) includes a controller that controls the position of an APU inlet door (138), and thus ram air flow to the APU (100), to ensure optimal starting conditions are attained and maintained in the APU (100) during APU startup operations. The controller receives a signal representative of an APU operational parameter (152) and, in response, to supplies APU inlet door (138) position commands. An APU inlet door actuator (142) is coupled to the APU inlet door (138) and, in response to the APU inlet door (138) position commands, moves the APU inlet door (138) to the commanded position.