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1.发明授权Pivoting door thrust reverser with controlled bypass through the rear portion of the thrust reverser door 失效枢转门推力反向器，带有控制旁路通过推力反向器门的后部
公开(公告)号：US5937636A
公开(公告)日：1999-08-17
申请号：US941633
申请日：1997-10-02
摘要： A thrust reverser is disclosed for an aircraft turbojet engine having a cowling with an inner surface forming an outer boundary of a gas flow duct, the cowling having at least one reverse thrust opening and a thrust reverser door pivotally attached to the cowling so as to move between a forward thrust position, wherein the thrust reverser door closes the at least one reverse thrust opening and a reverse thrust position, wherein a forward portion of the thrust reverser door moves outwardly from the cowing and a rear portion of the door moves inwardly into the gas flow duct so as to redirect a first portion of the gases flowing through the gas flow duct through the reverse thrust opening. The thrust reverser also includes a passageway bounded at least in part by the rear portion of the thrust reverser door located in the gas flow duct when the thrust reverser door is in the reverse thrust position, the passageway enabling a second portion of the gases flowing through the gas flow duct to pass to the rear of the thrust reverser door and to redirect this second portion of gases in an oblique direction relative to the gas flow duct to eliminate any forward thrust developed by the second portion of gases.
摘要翻译： 公开了一种用于具有整流罩的飞行器涡轮喷气发动机的推力反向器，其内表面形成气体流动管道的外边界，整流罩具有至少一个反向推力开口和枢转地附接到整流罩的推力反向器门，以便移动 在推进推力位置之间，其中推力反向器门关闭至少一个反向推力开口和反向推力位置，其中推力反向器门的前部部分从该起动器向外移动，并且该门的后部向内移动到 气流管道，以便使流经气流管道的气体的第一部分通过反向推力开口重定向。 推力反向器还包括至少部分由位于气体流动管道中的推力反向器门的后部限定的通道，当推力反向器门处于反向推力位置时，通道使第二部分气体流过 气体流动管道通过推力反向器门的后部，并且相对于气体流动管道在倾斜方向上将该第二部分气体重定向，以消除由第二部分气体产生的任何正向推力。
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2.发明申请REAR SECTION OF AIRCRAFT NACELLE AND NACELLE EQUIPPED WITH SUCH REAR SECTION 有权具有这种后部装备的空中客车和后舱的后部分公开(公告)号：US20120000179A1
公开(公告)日：2012-01-05
申请号：US12673288
申请日：2008-06-16
IPC分类号： F02K1/52
CPC分类号： B64D29/00
摘要： The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterised in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.
摘要翻译： 本发明涉及飞机机舱的后部（11），其包括两个半部（13a，13b），其限定：用于容纳涡轮喷气发动机（7）的中央部分（C），冷空气环形通道（31） 设置在所述中心部分（C）周围，以及设置在所述中心部分（C）下方的至少一个六小时空腔（15）。 后部分的特征在于它包括用于在所述环形通道（31）和所述六小时空腔（15）之间流体连通的至少一个管道（29a，29b），用于保持六小时空腔内的温度（15 ）在相对较低的范围内。
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3.发明申请JET ENGINE NACELLE EQUIPPED WITH A SYSTEM FOR MECHANICALLY INHIBITING A THRUST REVERSER 有权喷气式发动机装备有一个用于机械地阻止逆转器的系统公开(公告)号：US20110259435A1
公开(公告)日：2011-10-27
申请号：US12672101
申请日：2008-06-16
IPC分类号： B64D33/02
CPC分类号： B64D29/06 , B64D29/00 , F02K1/72 , F02K1/766 , Y10T137/0645
摘要： The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl (12) mounted translatably along at least one guide rail (15) in a direction substantially parallel to a longitudinal axis of the nacelle, said movable cowl being able to switch alternately from a closed position, in which it provides the nacelle with aerodynamic continuity and covers the deflection means, to an open position in which it opens a passage in the nacelle and uncovers said deflection means, the nacelle being characterized in that the aft section is equipped with at least one stud (18) mounted such that it can move over a fixed structure of the aft section in the region of the guide rail between a retracted position, in which said stud is withdrawn from the running track of the rail and allows a translational movement of the movable cowl, and an engaged position, in which it forms a stop capable of preventing the movable cowl from sliding in the downstream direction of the nacelle.
摘要翻译： 本发明涉及一种喷气式发动机机舱，其包括前进气进口部分，旨在围绕喷气式发动机风扇的中段，以及装备有至少一个推力反转系统的后部，其一方面包括用于偏转的装置 喷气发动机的空气流的至少一部分，另一方面，至少一个整流罩（12），其沿着基本上平行于所述机舱的纵向轴线的方向沿着至少一个导轨（15）平移地安装，所述整流罩 可移动整流罩能够从关闭位置交替地切换，其中它将机舱具有空气动力学连续性并且将偏转装置覆盖到打开位置，在该打开位置中，其打开机舱中的通道并且露出所述偏转装置，所述机舱被表征 其特征在于，所述后部装备有至少一个安装成使得其可以在所述导轨的区域中的所述后部的固定结构的缩回位置之间移动的螺柱（18），所述后部位置 所述螺柱从轨道的运行轨道中撤出，并允许可移动整流罩的平移运动和接合位置，其中它形成能够防止可移动整流罩在机舱的下游方向上滑动的止挡件。
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公开(公告)号：US6148607A
公开(公告)日：2000-11-21
申请号：US113323
申请日：1998-07-10
摘要： A thrust reverser for aircraft gas-turbine engines includes latch devices that display a tell-tale visible indication when thrust reverser shutters (doors, etc.) are ajar. A latch of the lock at least partly projects from a wall (13, 14) radially bounding the annular structure (12) of the thrust reverser (10) when the latch (37) is in the open mode.
摘要翻译： 用于飞机燃气涡轮发动机的推力反向器包括闩锁装置，当推力反向开关（门等）为止时，该装置显示出可见的指示。 当闩锁（37）处于打开模式时，锁的闩锁至少部分地从径向地包围推力反向器（10）的环形结构（12）的壁（13,14）突出。
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公开(公告)号：US5987881A
公开(公告)日：1999-11-23
申请号：US041767
申请日：1998-03-13
CPC分类号： F02K1/70 , Y02T50/672
摘要： A thrust reverser is disclosed for an aircraft jet engine having a cowling with an outer surface and at least one reverse thrust opening, the thrust reverser including a thrust reverser door assembly movable with respect to the cowling between a forward thrust position, in which the reverse thrust opening is uncovered, and a reverse thrust position in which the thrust reverser door uncovers the reverse thrust opening. The thrust reverser door assembly includes an inner structure, an external panel movably connected to the inner structure and one or more resilient devices acting on the inner structure and the external panel to bias the external panel toward the inner structure such that, when the thrust reverser door is in the forward thrust position the external panel is displaced away from the inner structure by contact with the cowling such that an outer surface of the external panel is substantially flush with the outer surface of the cowling.
摘要翻译： 公开了一种用于具有外表面和至少一个反推力开口的整流罩的飞机喷气发动机的推力反向器，推力反向器包括可在前推力位置之间相对于整流罩移动的推力反向器门组件，其中相反 推力开口未被覆盖，并且反推力位置中，推力反向器门揭开反向推力开口。 推力反向器门组件包括内部结构，可移动地连接到内部结构的外部面板和作用在内部结构上的一个或多个弹性装置和外部面板，以将外部面板偏向内部结构，使得当推力反向器 门处于向前推力位置，外部板通过与整流罩接触而远离内部结构移位，使得外部面板的外表面与整流罩的外表面基本齐平。
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6.发明授权公开(公告)号：US08943793B2
公开(公告)日：2015-02-03
申请号：US12673288
申请日：2008-06-16
CPC分类号： B64D29/00
摘要： The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterized in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.
摘要翻译： 本发明涉及飞机机舱的后部（11），其包括两个半部（13a，13b），其限定：用于容纳涡轮喷气发动机（7）的中央部分（C），冷空气环形通道（31） 设置在所述中心部分（C）周围，以及设置在所述中心部分（C）下方的至少一个六小时空腔（15）。 后部分的特征在于它包括用于在所述环形通道（31）和所述六小时空腔（15）之间流体连通的至少一个管道（29a，29b），用于保持六小时空腔内的温度（15 ）在相对较低的范围内。
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公开(公告)号：US6094908A
公开(公告)日：2000-08-01
申请号：US34140
申请日：1998-02-23
CPC分类号： F02K1/76 , F02K1/70 , Y02T50/671
摘要： A thrust reverser is disclosed for a high bypass ratio turbofan jet engine having a cowling with an inner surface forming an outer boundary of a gas flow duct, the cowling having a plurality of lateral openings and a plurality of thrust reverser doors connected to the cowling so as to be movable between forward thrust positions and reverse thrust positions. The thrust reverser also includes a plurality of linear actuators, one linear actuator connected to the cowling and to each thrust reverser door so as to move the thrust reverser doors between their forward and reverse thrust positions. A synchronization system is included in the thrust reverser and interconnects two of the plurality of linear actuators, the synchronization system having an electric motor, a plurality of transmission drive links, each transmission drive link having one end connected to one of the two linear actuators and a second end, and a gear drive mechanism connecting the output of the electric motor to the second ends of the transmission drive links. Operation of the electric motor rotates the transmission drive links to operate the respective linear actuators to move the thrust reverser doors between their forward and reverse thrust positions. The gear drive mechanism and the connections between the transmission drive links and the linear actuators are such that, in the absence of rotation of the transmission drive links, operation of the linear actuators is prohibited, thereby locking the thrust reverser doors in their forward thrust positions.
摘要翻译： 公开了一种用于具有整流罩的高旁路比涡轮风扇喷气发动机的推力反向器，其内表面形成气体流动管道的外边界，整流罩具有多个侧向开口和多个与整流罩相连的推力反向器门 以便在前推力位置和反推力位置之间移动。 推力反向器还包括多个线性致动器，一个线性致动器，其连接到整流罩和每个推力反向器门，以便将推力反向器门在它们的向前和反向推力位置之间移动。 同步系统包括在推力反向器中并且互连多个线性致动器中的两个，同步系统具有电动机，多个传动驱动连杆，每个传动驱动连杆的一端连接到两个线性致动器之一， 第二端和将电动机的输出连接到变速器驱动连杆的第二端的齿轮驱动机构。 电动机的操作使变速器驱动链路旋转，以操作相应的线性致动器，以使推力反向器门在它们的向前和反向推力位置之间移动。 齿轮驱动机构以及传动驱动连杆和线性致动器之间的连接使得在没有变速器传动链节的旋转的情况下，禁止线性致动器的操作，从而将推力反向器门锁定在它们的向前推力位置 。
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8.发明授权Aircraft engine ducted fan cowling with thrust reverser section and fairings for fan shroud brace members in fan exhaust duct 失效飞机发动机风扇整流罩带推力反向器部分和整流罩，用于风扇排气管道中的风扇罩支架构件
公开(公告)号：US6068213A
公开(公告)日：2000-05-30
申请号：US96293
申请日：1998-06-12
CPC分类号： F02K1/52 , Y02T50/672
摘要： A ducted fan aircraft turbojet engine having an inner engine core cowling, an outer fan shroud, an outer fan outlet cowling including a thrust reverser, a fan exhaust duct between the inner engine core cowling and the outer fan outlet cowling, at least one fan shroud brace connecting the engine and the outer fan shroud, and at least one fairing element extending into and along the fan exhaust duct and located directly adjacent and rearwardly of the at least one fan shroud brace. The at least one fairing may be connected directly to the at least one fan shroud brace, the inner engine core cowling or the outer fan outlet cowling. The invention has utility where the fan outlet cowling and thrust reverser are mounted independently of the inner engine core cowling over their respective inner areas.
摘要翻译： 一种具有内部发动机芯整流罩，外部风扇罩，包括推力反向器的外部风扇出口整流罩，内部发动机芯整流罩和外部风扇出口整流罩之间的风扇排放管道的管道式风扇飞行器涡轮喷气发动机，至少一个风扇罩 连接发动机和外风扇护罩的支架，以及至少一个整流罩元件，其延伸到风扇排气管道中并且沿风扇排气管道延伸并且定位成直接邻近和向后至少一个风扇护罩支架。 至少一个整流罩可以直接连接到至少一个风扇护罩支架，内部发动机芯整流罩或外部风扇出口整流罩。 本发明具有这样的用途，其中风扇出口整流罩和推力反向器独立于内部发动机芯整流罩安装在它们各自的内部区域上。
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公开(公告)号：US6045091A
公开(公告)日：2000-04-04
申请号：US113319
申请日：1998-07-10
摘要： An aircraft gas turbine-engine thrust-reverser specifically designed to withstand impacts possibly caused by objects propelled from the engines around which they are mounted, for instance disk or blade fragments. These impacts have the energy to distort the annular thrust-reverser structure or to break its bracing components. An emergency locking system for such thrust reverser (35) each comprises a hinging latch (38) of which one end is in the form of a hook (40) partly enclosing the lock-interfacing mechanism (43) with the latch (38) being automatically biased into closing by an elastic arrangement (47). Such a configuration allows setting up additional mechanical connections which are able to compensate for any distortion of the thrust-reverser's annular structure or for any ruptured bracing component in the event of impact by an engine piece.
摘要翻译： 飞机燃气轮机 - 发动机推力反向器专门设计用于承受可能由其所安装的发动机推进的物体（例如盘片或叶片碎片）引起的冲击。 这些冲击具有扭曲环形推力反向器结构或破坏其支撑部件的能量。 用于这种推力反向器（35）的紧急锁定系统各自包括铰接闩锁（38），其一端呈部分地围绕锁定接合机构（43）的钩（40）的形式，闩锁（38）为 通过弹性装置（47）自动地偏向关闭。 这种构造允许建立额外的机械连接，其能够补偿推力反向器的环形结构的任何变形，或者在发动机件碰撞的情况下，任何破裂的支撑部件。
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10.发明授权Locking system for an aircraft jet engine thrust reverser door including a plurality of locking devices arranged to prevent deformation of the thrust reverser door 失效包括用于防止推力反向器门变形的多个锁定装置的用于飞机喷气发动机推力反向器门的锁定系统
公开(公告)号：US6044641A
公开(公告)日：2000-04-04
申请号：US980618
申请日：1997-12-01
CPC分类号： F02K1/766 , F02K1/70 , Y02T50/671
摘要： A locking system is disclosed for an aircraft jet engine thrust reverser door that is movably connected to an engine cowling so as to be movable between a forward thrust position and a reverse thrust position, the cowling having a reverse thrust opening that is covered by the thrust reverser door when in the forward thrust position and uncovered when the thrust reverser door is in the reverse thrust position. The locking system has a plurality of locking devices attached to the cowling at the forward side of the reverse thrust opening with at least one locking device located on opposite sides of a longitudinal line equidistantly spaced from opposite lateral sides of the thrust reverser door such that the locking devices simultaneously lock the thrust reverser door in the forward thrust position.
摘要翻译： 公开了一种用于飞机喷气发动机推力反向器门的锁定系统，其可移动地连接到发动机整流罩，以便能够在向前推力位置和反向推力位置之间移动，所述整流罩具有被推力覆盖的反向推力开口 在向前推力位置时，反向门，当推力反向器门处于反向推力位置时未翻盖。 锁定系统具有多个锁定装置，其在逆向推力开口的前侧附接到整流罩，具有位于与推力反向器门的相对侧边等距离间隔开的纵向线的相对侧上的至少一个锁定装置，使得 锁定装置同时将推力反向器门锁定在向前推力位置。
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