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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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公开(公告)号：US06170255B2
公开(公告)日：2001-01-09
申请号：US09381968
申请日：1999-10-01
IPC分类号： F02K170
CPC分类号： F02K1/70
摘要： A thrust reverser for a turbojet engine comprising displaceable downstream baffles (2) which are integrated into the outer wall of the annular bypass-flow duct so as to form the downstream end of the exhaust nozzle of the turbojet engine during the operation of the turbojet engine in a forward-thrust mode is provided. When in a thrust-reversal mode, the downstream baffles (2) are positioned so as to deflect the bypass flow and obtain thrust reversal. The baffles (2) are pivotably mounted on stationary pivots (10) and have at least one associated displacement mechanism (6, 7) for driving the baffles (2). Each downstream baffle (2) has an associated displaceable inner panel (13). Each baffle (2) and the associated inner panel (13) are driven through different angular displacements by the at least one associated displacement mechanism (6, 7), which is common to the baffle (2) and the associated inner panel (13), to change between the forward-thrust mode and the thrust-reversal mode. The at least one associated displacement mechanism (6, 7) is preferably mounted in a stationary manner on a stationary structure of the thrust reverser.
摘要翻译： 一种用于涡轮喷气发动机的推力反向器，包括可移动的下游挡板（2），其集成在环形旁通管道的外壁中，以便在涡轮喷气发动机的操作期间形成涡轮喷气发动机的排气喷嘴的下游端 提供了向前推力模式。 当处于推力反转模式时，下游挡板（2）被定位成偏转旁路流并获得推力反向。 挡板（2）可枢转地安装在固定枢轴（10）上并具有用于驱动挡板（2）的至少一个相关联的移动机构（6,7）。 每个下游挡板（2）具有相关联的可移动内板（13）。 每个挡板（2）和相关联的内板（13）通过与挡板（2）和相关联的内板（13）共同的至少一个相关联的位移机构（6,7）被驱动通过不同的角位移， 在正向推力模式和推力反转模式之间切换。 至少一个相关联的移动机构（6,7）优选地以固定的方式安装在推力反向器的固定结构上。
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公开(公告)号：US6145786A
公开(公告)日：2000-11-14
申请号：US53776
申请日：1998-04-02
摘要： A latching mechanism is disclosed for a jet engine thrust reverser having a thrust reverser door movably connected to an engine cowling with a reverse thrust opening, the thrust reverser door being movable between a forward thrust position, in which the thrust reverser door covers the reverse thrust opening, and a reverse thrust position, in which the reverse thrust opening is uncovered. The latching mechanism has a lock bar mounted on the thrust reverser door, the lock bar having a distal end, and a latch member pivotally located on the cowling, the latch member having a slot engaged by the distal end of the lock bar when the thrust reverser door is in the forward thrust position. The latch member is movable between a latched position, in which the latch member prevents disengagement of the distal end of the lock bar from the slot, so as to lock the thrust reverser door in the forward thrust position, and an unlatched position which permits disengagement of the distal end of the lock bar from the slot. The latching mechanism also includes a hook member connected to the cowling and located so as to engage the distal end of the lock bar upon relative movement between the cowling and the thrust reverser door away from each other in a direction generally parallel to a longitudinal axis of the cowling, such engagement preventing disengagement of the distal end of the lock bar from the slot and displacement of the thrust reverser door from the forward thrust position.
摘要翻译： 公开了一种用于喷气发动机推力反向器的闩锁机构，其具有可逆转地连接到具有反推力开口的发动机整流罩的推力反向器门，推力反向器门可在向前推力位置之间移动，推力反向器门覆盖反向推力 开启和反推力位置，其中反推力开口未被覆盖。 闩锁机构具有安装在推力反向器门上的锁杆，锁定杆具有远端，并且枢转地位于整流罩上的闩锁构件，闩锁构件具有与锁定杆的远端接合的槽，当推力 反向门处于向前推力位置。 闩锁构件可以在闩锁位置之间移动，在该闩锁位置中，闩锁构件防止锁定杆的远端从槽中脱离，以便将推力反向器门锁定在向前推力位置，并且允许脱开的解锁位置 的锁定杆的远端与狭槽。 闩锁机构还包括连接到整流罩的钩构件，并且定位成在整流罩和推力反向器门之间相对运动时在大致平行于纵向轴线的方向上彼此远离的方向上与锁定杆的远端接合 整流罩，这种接合防止锁定杆的远端脱离槽并且推力反向器门从向前的推力位置移位。
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公开(公告)号：US6029439A
公开(公告)日：2000-02-29
申请号：US988957
申请日：1997-12-11
CPC分类号： F02K1/70
摘要： A gas flow guide is disclosed for an aircraft jet engine thrust reverser having a thrust reverser door movably connected to a cowling so as to move between forward and reverse thrust positions, the cowling having a reverse thrust opening bounded by a forward edge having a deflector, an opposite lateral side edges, an inner surface of the cowling forming an outer boundary of a gas flow duct, a forward inner surface of the thrust reverser door tapering toward an outer surface so as to form a cavity opening into the gas flow duct when the thrust reverser door is in the forward thrust position, wherein the gas flow guide has at least one guide vane connected to the cowling so as to be located within the cavity when the thrust reverser door is in the forward thrust position and located rearwardly of the deflector extending from the forward edge so as to guide the gas passing through the reverse thrust opening when the thrust reverser door is in the reverse 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的气流引导器，其具有可移动地连接到整流罩的推力反向器门，以便在前进和反向推力位置之间移动，整流罩具有由具有偏转器的前边缘限定的反向推力开口， 整流罩的内表面形成气流管道的外边界，推力反向器门的前内表面朝向外表面逐渐变细，以形成通向气流管道的空腔 推力反向器门处于向前推力位置，其中气体导流器具有连接到整流罩的至少一个导向叶片，以便当推力反向器门处于向前推力位置并位于偏转器后面时位于腔体内 从前缘延伸，以便当推力反向器门处于反向推力位置时引导通过反向推力开口的气体。
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公开(公告)号：US5893265A
公开(公告)日：1999-04-13
申请号：US853935
申请日：1997-05-09
CPC分类号： F02K1/70 , Y02T50/671
摘要： The present invention relates to a thrust reverser for a turbojet engine having a cowling bounding a flow duct through which gases flow from the front of the cowling towards a rear of the cowling, the cowling having at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser has a thrust reverser door pivotally mounted on the cowling so as to be movable between a forward and a thrust position, wherein the thrust reverser door covers the reverse thrust opening, and a reverse thrust position wherein the thrust reverser door uncovers the reverse thrust opening and directs at least a portion of the gases flowing through the gas flow duct outwardly through the reverse thrust opening. A vane having an air foil cross-sectional configuration is connected to the thrust reverser door and is located so as to be acted on by the gases passing through the gas flow duct when the thrust reverser door is adjacent to its forward thrust position, such that the vane exerts a force on the thrust reverser door urging it toward its forward thrust position.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的推力反向器，其具有围绕流动管道的整流罩，气体通过该流动管道从整流罩的前部流向整流罩的后部，整流罩具有至少一个与气流连通的反向推力开口 管。 推力反向器具有枢转地安装在整流罩上的推力反向器门，以便能够在前进位置和推力位置之间移动，其中推力反向器门覆盖反向推力开口，以及反推力位置，其中推力反向器门揭开反向 推力打开并且引导至少一部分气体通过反向推力开口向外流过气体流动管道。 具有空气箔横截面构造的叶片连接到推力反向器门，并且当推力反向器门邻近其向前推力位置时被定位成被通过气体流动管道的气体作用，使得 叶片在推力反向器门上施加力，将其推向其向前的推力位置。
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公开(公告)号：US08640825B2
公开(公告)日：2014-02-04
申请号：US13000720
申请日：2009-05-14
申请人： Guy Bernard Vauchel , Emmanuel Drevon , Patrick Gonidec , Guillaume Ruckert , Eric Conete , Renaud Barreteau
发明人： Guy Bernard Vauchel , Emmanuel Drevon , Patrick Gonidec , Guillaume Ruckert , Eric Conete , Renaud Barreteau
IPC分类号： E04B1/84
CPC分类号： G10K11/172 , B64D33/06 , F02K1/827 , F02K3/06 , F05D2300/501 , Y02T50/672
摘要： The invention relates to an acoustic panel (20) for an ejector nozzle (10) comprising the following main components: an external skin (22) containing acoustic holes (29); an internal skin (23); an acoustic structure (21) comprising alveolar-core cells (27) between the internal skin (23) and the external skin (22). At least one main component selected from the external skin (22), the internal skin (23) and the acoustic structure (21) is formed by a composite material and the acoustic structure (21) is held in contact with either or both of the internal (23) and external (22) skins by compression by elastic means and/or by fixing by mechanical fixing means (24). The invention also relates to an injector nozzle (10) and a nacelle (1) comprising such an acoustic panel (20).
摘要翻译： 本发明涉及一种用于喷射器喷嘴（10）的声学面板（20），其包括以下主要部件：包含声孔（29）的外部皮肤（22）; 内部皮肤（23）; 在所述内部皮肤（23）和所述外部皮肤（22）之间包括肺泡细胞（27）的声学结构（21）。 从外部皮肤（22），内部皮肤（23）和声音结构（21）中选择的至少一个主要部件由复合材料形成，声学结构（21）保持与 内部（23）和外部（22）表面通过弹性装置压缩和/或通过机械固定装置（24）固定。 本发明还涉及一种喷射器喷嘴（10）和包括这种声学面板（20）的机舱（1）。
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公开(公告)号：US20110108357A1
公开(公告)日：2011-05-12
申请号：US13000720
申请日：2009-05-14
申请人： Guy Bernard Vauchel , Emmanuel Drevon , Patrick Gonidec , Guillaume Ruckert , Eric Conete , Renaud Barreteau
发明人： Guy Bernard Vauchel , Emmanuel Drevon , Patrick Gonidec , Guillaume Ruckert , Eric Conete , Renaud Barreteau
CPC分类号： G10K11/172 , B64D33/06 , F02K1/827 , F02K3/06 , F05D2300/501 , Y02T50/672
摘要： The invention relates to an acoustic panel (20) for an ejector nozzle (10) comprising the following main components: an external skin (22) containing acoustic holes (29); an internal skin (23); an acoustic structure (21) comprising alveolar-core cells (27) between the internal skin (23) and the external skin (22). At least one main component selected from the external skin (22), the internal skin (23) and the acoustic structure (21) is formed by a composite material and the acoustic structure (21) is held in contact with either or both of the internal (23) and external (22) skins by compression by elastic means and/or by fixing by mechanical fixing means (24). The invention also relates to an injector nozzle (10) and a nacelle (1) comprising such an acoustic panel (20).
摘要翻译： 本发明涉及一种用于喷射器喷嘴（10）的声学面板（20），其包括以下主要部件：包含声孔（29）的外部皮肤（22）; 内部皮肤（23）; 在所述内部皮肤（23）和所述外部皮肤（22）之间包括肺泡细胞（27）的声学结构（21）。 从外部皮肤（22），内部皮肤（23）和声音结构（21）中选择的至少一个主要部件由复合材料形成，声学结构（21）保持与 内部（23）和外部（22）表面通过弹性装置压缩和/或通过机械固定装置（24）固定。 本发明还涉及一种喷射器喷嘴（10）和包括这种声学面板（20）的机舱（1）。
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9.发明授权Turbojet-engine thrust reverser with scoop-doors of adjustable exhaust cross-section 失效涡轮喷气发动机推力反向器，带有可调节排气横截面的铲斗
公开(公告)号：US6158211A
公开(公告)日：2000-12-12
申请号：US333921
申请日：1999-06-16
申请人： Patrick Gonidec , Jean Fabrice Marcel Portal , Vincent Joseph Rodolphe Studer , Guy Bernard Vauchel
发明人： Patrick Gonidec , Jean Fabrice Marcel Portal , Vincent Joseph Rodolphe Studer , Guy Bernard Vauchel
IPC分类号： F02K1/70
CPC分类号： F02K1/70
摘要： A bypass turbojet-engine thrust reverser comprises at least one hollow, pivoting door (3) with an inner conduit (10), defined between an outer structure (4) of the door (3) and an inner structure (5) of the door (3), which guides flow through the door (3) when the door (3) is in a reverse thrust position. At least a downstream part of the outer structure (4) of the door (3) is independent of and displaceable relative to the inner structure (5) of the door (3) and is driven in a centrifugal direction relative to the inner structure (5) by a mechanical drive system such that a downstream exhaust cross-section (S2) of the inner conduit (10), which is less than an intake cross-section (S1) of the inner conduit (10) when the door (3) is in a forward thrust position, is at least equal to the intake cross-section (S1) when the door (3) is in the reverse thrust position.
摘要翻译： 旁通涡轮喷气发动机推力反向器包括至少一个中空的枢转门（3），其具有限定在门（3）的外部结构（4）与门的内部结构（5）之间的内部导管（10） （3），当门（3）处于反推力位置时，其引导流过门（3）。 门（3）的外部结构（4）的至少下游部分相对于门（3）的内部结构（5）是独立的并且可相对于门（3）的内部结构（5）移动，并且相对于内部结构 通过机械驱动系统，使得当内部导管（10）的下游排气横截面（S2）小于门（3）内部导管（10）的进气横截面（S1）时， ）处于向前推力位置时，当门（3）处于反向推力位置时，至少等于进气横截面（S1）。
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10.发明授权
公开(公告)号：US6019397A
公开(公告)日：2000-02-01
申请号：US98564
申请日：1998-06-17
CPC分类号： F16L39/00
摘要： A security hydraulic coupling system includes at least two hydraulic connector fittings (4, 5) which may be connected to adjacent fluid ports (1, 2) of a hydraulic unit (12) and which are linked to each other by means of a base plate (3) which is also shaped to cooperate with at least one projection (10) on the hydraulic unit (12) to thereby physically prescribe the positions of the various elements during the steps of fitting connection and disconnection. An interlock system comprises a security pin (6) which is housed in the base plate (3) and is mounted between the fittings (4, 5) and cooperates with grooves (7, 8) provided in the fittings (4, 5) to prescribe the possible sequence of steps in connecting/disconnecting the fittings (4, 5) from the ports of the hydraulic unit (12).
摘要翻译： 安全液压耦合系统包括至少两个液压连接器配件（4,5），其可以连接到液压单元（12）的相邻流体端口（1,2），并且通过底板 （3），其也被成形为与液压单元（12）上的至少一个突起（10）配合，从而在装配连接和断开的步骤期间物理地规定各种元件的位置。 联锁系统包括安全销（6），其安装在基板（3）中并安装在配件（4,5）之间，并与设置在配件（4,5）中的槽（7,8）配合， 规定从液压单元（12）的端口连接/断开接头（4,5）的可能顺序。
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