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1. 发明授权

US5775097A Turbojet engine thrust reverser with biased baffles 失效
标题翻译：涡轮喷气发动机推力反向器带偏压挡板
公开(公告)号：US5775097A
公开(公告)日：1998-07-07
申请号：US748910
申请日：1996-11-15
申请人： Pascal Lardy , Laurent Georges Valleroy , Guy Bernard Vauchel
发明人： Pascal Lardy , Laurent Georges Valleroy , Guy Bernard Vauchel
IPC分类号： F02K1/60 , F02K1/54
CPC分类号： F02K1/60 , Y02T50/671
摘要： A thrust reverser is disclosed for a turbojet engine having a nacelle with a plurality of beams extending rearwardly from a rear portion of the nacelle on which are pivotally mounted thrust reverser baffles movable between forward thrust positions and reverse thrust positions. The thrust reverser baffles have forward edges, rear edges forming a portion of an exhaust nozzle when the baffles are in their forward thrust positions, outer baffle surfaces substantially flush with the outer surface of the nacelle when the baffles are in their forward thrust positions, and inner baffle surfaces forming a portion of a gas flow duct when the baffles are in their forward thrust positions, such that the exhaust nozzle has a width H measured in a direction parallel to the width of the beam h such that h is equal or greater than 0.6 H. In order to bias the thrust reverser baffles to remain in their forward thrust positions, the gases within the gas flow duct are prevented from acting on forward portions of the thrust reverser baffles when the baffles are in their forward thrust positions such that the resultant forces of the gases in the gas flow duct acting on the inner baffle surfaces when the baffles are in their forward thrust positions urge the baffles to remain in their forward thrust positions.
摘要翻译：公开了一种用于具有机舱的涡轮喷气发动机的推力反向器，其具有从机舱的后部向后延伸的多个梁，在所述机舱的后部可转动地安装有推力反向挡板，其可在前推力位置和反推力位置之间移动。推力反向挡板具有前边缘，当挡板处于其向前推力位置时，后边缘形成排气喷嘴的一部分，当挡板处于其向前推力位置时，外挡板表面基本上与机舱的外表面齐平;以及当所述挡板处于其向前推力位置时，形成气流管道的一部分的内挡板表面，使得所述排气喷嘴具有在平行于所述梁h的宽度的方向上测量的宽度H，使得h等于或大于为了使推力反向器挡板偏置以保持其向前的推力位置，当挡板处于其向前推力位置时，气流管道内的气体被阻止作用在推力反向挡板的前部，使得当挡板处于向前推力位置时，作用在内挡板表面上的气流通道中的气体的合力促使挡板保持在t 后继推进位置。

2. 发明授权

US08985506B2 Air intake for aircraft nacelle, and propulsion assembly including such air intake 有权
标题翻译：飞机机舱的进气口和包括这种进气口的推进装置
公开(公告)号：US08985506B2
公开(公告)日：2015-03-24
申请号：US12864901
申请日：2009-01-21
申请人： Guy Bernard Vauchel , Laurent Georges Valleroy , Stéphane Beilliard , Fabien Bravin
发明人： Guy Bernard Vauchel , Laurent Georges Valleroy , Stéphane Beilliard , Fabien Bravin
IPC分类号： B64D33/02 , F01D21/00 , F02C7/045
CPC分类号： B64D33/02 , B64D2033/0206 , B64D2033/0286 , F01D21/00 , F02C7/045 , F05D2220/36
摘要： The invention relates to an air intake for an aircraft nacelle that includes a shroud that can be mounted on the fan casing of a turbojet engine. The shroud is sized so as to define a circumferential gap relative to the casing. Punctual linking means between the shroud and the casing are discretely distributed at the periphery of the shroud.
摘要翻译：本发明涉及一种用于飞机机舱的进气口，其包括可安装在涡轮喷气发动机的风扇壳体上的护罩。护罩的尺寸设定成相对于外壳限定圆周间隙。护罩和外壳之间的准时连接装置离散地分布在护罩的周边。

3. 发明申请

US20100320316A1 AIR INTAKE FOR AIRCRAFT NACELLE, AND PROPULSION ASSEMBLY INCLUDING SUCH AIR INTAKE 有权
标题翻译：航空器空气调节器和推进装置，包括这样的进气
公开(公告)号：US20100320316A1
公开(公告)日：2010-12-23
申请号：US12864901
申请日：2009-01-21
申请人： Guy Bernard Vauchel , Laurent Georges Valleroy , Stéphane Beilliard , Fabien Bravin
发明人： Guy Bernard Vauchel , Laurent Georges Valleroy , Stéphane Beilliard , Fabien Bravin
IPC分类号： B64D33/02 , B64C1/40
CPC分类号： B64D33/02 , B64D2033/0206 , B64D2033/0286 , F01D21/00 , F02C7/045 , F05D2220/36
摘要： The invention relates to an air intake for an aircraft nacelle that comprises a shroud (19) that can be mounted on the fan casing (15) of a turbojet engine (1). The shroud (19) is sized so as to define a circumferential gap (J) relative to the casing (15). Punctual linking means (27, 33) between the shroud (19) and the casing (15) are discretely distributed at the periphery of said shroud (19).
摘要翻译：本发明涉及一种用于飞机机舱的进气口，其包括可安装在涡轮喷气发动机（1）的风扇壳体（15）上的护罩（19）。护罩（19）的尺寸被设计成相对于壳体（15）限定圆周间隙（J）。护罩（19）与壳体（15）之间的准时连接装置（27,33）离散分布在所述护罩（19）的周边。

4. 发明授权

US5727380A Turbojet engine thrust reverser with asymmetrical doors 失效
标题翻译：涡轮喷气发动机推力反向器具有不对称门
公开(公告)号：US5727380A
公开(公告)日：1998-03-17
申请号：US677721
申请日：1996-07-08
申请人： Pascal Lardy , Guy Bernard Vauchel
发明人： Pascal Lardy , Guy Bernard Vauchel
IPC分类号： F02K1/62 , F02K1/56 , F02K1/70 , F02K1/00
CPC分类号： F02K1/563 , F02K1/70
摘要： A thrust reverser is disclosed for a turbofan-type turbojet engine having a cowling bounding a gas flow duct in which the thrust reverser has a plurality of thrust reverser doors each pivotally attached to the cowling so as to be movable between a forward thrust position and a reverse thrust position which redirects the gases passing through the gas flow duct outwardly from the cowling to produce a reverse thrust. At least one of the plurality of thrust reverser doors having a width, measured in a generally circumferential direction around the cowling, less than a corresponding width of at least one of the other thrust reverser doors.
摘要翻译：公开了一种用于涡轮风扇式涡轮喷气发动机的推力反向器，其具有围绕气体流动管道的整流罩，其中推力反向器具有多个推力反向器门，每个推力反向器门可枢转地附接到整流罩，以便能够在前推力位置和反向推力位置，其将通过气体流动管道的气体从整流罩向外重新定向以产生反向推力。所述多个推力反向器门中的至少一个具有围绕所述整流罩的大致圆周方向测量的宽度小于其它推力反向器门中的至少一个的对应宽度。

5. 发明授权

US09206765B2 Thrust reversing device including variable nozzle section having first position for variation of the nozzle section and a second position for blocking a cold flow jet 有权
标题翻译：推力换向装置包括具有用于改变喷嘴部分的第一位置的可变喷嘴部分和用于阻挡冷流喷射的第二位置
公开(公告)号：US09206765B2
公开(公告)日：2015-12-08
申请号：US13321831
申请日：2010-05-18
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： F02K1/72 , F02K1/76
CPC分类号： F02K1/72 , F02K1/763 , F05D2270/66 , Y10T74/18576
摘要： The invention relates to a thrust reversing device (20) that includes at least one mobile cowling (30) mounted in translation in a direction substantially parallel to a longitudinal axis of a nacelle, capable of moving alternatively from a closing position on which it enables the aerodynamic continuity of the nacelle into an opening position in which it opens a passage in the nacelle for the bypassed flow, wherein said mobile cowling (30) also includes as an extension at least one variable nozzle section (40) including at least one panel (41) mounted so as to be capable of rotation, the panel (41) being adapted for pivoting towards at least one position entailing a variation in the nozzle section (40) on the one hand, and pivoting towards a position in which it blocks a cold flow jet (13) formed between a fixed structure of a turbojet fairing (12 and the nacelle on the other hand, wherein the mobile cowling (30) and the panel (41) are associated with actuation means (50) capable of activating the respective translation and rotation movements thereof, characterized in that said actuation means (50) are connected to an upstream end of the panel (41) by a driving connection rod (61) capable of moving about anchoring points respectively on the corresponding panel (41) and the associated actuation means (50).
摘要翻译：本发明涉及一种推力反向装置（20），其包括至少一个可移动的整流罩（30），该移动整流罩（30）在基本上平行于机舱的纵向轴线的方向上平移地安装，能够从关闭位置交替移动，空气动力学连续性的机舱进入打开位置，在打开位置中，其打开用于旁路流的机舱中的通道，其中所述可移动整流罩（30）还包括作为延伸部的至少一个可变喷嘴部分（40），其包括至少一个面板 41）被安装成能够旋转，所述面板（41）适于朝着至少一个位置枢转，所述至少一个位置一方面导致喷嘴部分（40）的变化，并且朝向其阻挡一个位置的位置枢转形成在涡轮喷气整流装置（12和机舱之间）的固定结构之间的冷流射流（13），其中可移动罩（30）和面板（41）与能够作用的致动装置其特征在于，所述致动装置（50）通过驱动连接杆（61）连接到所述面板（41）的上游端，所述驱动连接杆能够分别在相应的面板上 41）和相关联的致动装置（50）。

6. 发明授权

US09169805B2 Thrust inverter with translatable cascade vanes having detachable front frame 有权
标题翻译：具有可拆卸叶片的推力变频器具有可拆卸的前框架
公开(公告)号：US09169805B2
公开(公告)日：2015-10-27
申请号：US13510352
申请日：2010-10-26
申请人： Guy Bernard Vauchel , Pierre Caruel , Andre Baillard , Peter Sagat
发明人： Guy Bernard Vauchel , Pierre Caruel , Andre Baillard , Peter Sagat
IPC分类号： F01D25/28 , B64D29/08 , F02K1/72 , F02K1/68 , F02K1/54 , F01D25/24 , F02K1/64 , F02C7/20 , B64D29/06
CPC分类号： F02K1/72 , B64D29/06 , B64D29/08 , F01D25/24 , F01D25/243 , F01D25/28 , F02C7/20 , F02K1/54 , F02K1/64 , F02K1/68 , F05D2250/34
摘要： A thrust inverter for a turbojet engine nacelle includes an outer movable cowl and a front frame. The outer movable cowl translates between a closed position and a thrust inversion position and also moves to a supporting position in which the outer movable cowl is hinged and guided by a guiding member located on a pylon. In particular, the front frame holding cascade vanes is mounted downstream from an air blower housing, and part of the front frame is detachably connected to the air blower housing. The front frame is translatable along the guiding member once the front frame is detached from the air blower housing.
摘要翻译：用于涡轮喷气发动机机舱的推力逆变器包括外部可移动整流罩和前部框架。外部可移动整流罩在关闭位置和推力反转位置之间平移，并且还移动到支撑位置，在该支撑位置，外部可移动整流罩由位于塔架上的引导构件铰接并引导。具体地说，前端框架保持级联叶片安装在鼓风机壳体的下游，并且前框架的一部分可拆卸地连接到鼓风机壳体。一旦前框架与鼓风机壳体分离，前框架可沿引导构件平移。

7. 发明授权

US08919693B2 Lockable guiding system for a mobile part of a nacelle 有权
标题翻译：机舱移动部件的可锁定导向系统
公开(公告)号：US08919693B2
公开(公告)日：2014-12-30
申请号：US12531526
申请日：2008-03-07
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： B64D29/00 , B64D33/02 , F02C7/04 , B64D29/06 , B64D29/08 , E05F5/00
CPC分类号： F02C7/04 , B64D29/00 , B64D29/06 , B64D29/08 , E05F5/003 , E05Y2900/502 , F05D2240/14 , F05D2260/52
摘要： The invention relates to a guiding device (100) for part of a jet engine nacelle that can move in translation, comprising: (i) a rail (101) fixedly mounted on part of the nacelle, and (ii) a slide (102) which is connected to the mobile part and which can slide along the rail. The invention is characterized in that the guiding device is provided with a built-in retractable system for preventing the translational movement of the slide, for which purpose the device includes: (i) at least one blocking means (104) mounted such that it can move on the rail and occupy alternatively an engaged position in which it forms a translational abutment for the slide and a released position in which it is moved away from the slide and enables the relative translational movement of the slide beyond the locking system, and (ii) at least one means (130) for controlling the blocking means.
摘要翻译：本发明涉及一种可移动平移的部分喷气发动机机舱的引导装置（100），包括：（i）固定地安装在机舱的一部分上的导轨（101），和（ii）滑块（102）其连接到移动部件并且可以沿着轨道滑动。本发明的特征在于，引导装置设置有内置的可伸缩系统，用于防止滑块的平移运动，为此目的，该装置包括：（i）安装至少一个阻挡装置（104），使得其可在轨道上移动并且占据可选择的接合位置，在该位置中，其形成用于滑动件的平移邻接件和释放位置，其中滑动件移动远离滑动件，并且使得滑块相对于平移运动超过锁定系统，并且（ii ）至少一个用于控制阻挡装置的装置（130）。

8. 发明授权

US08740137B2 Removable air intake structure for a turbofan engine nacelle 有权
标题翻译：涡轮风扇发动机舱的可拆卸进气结构
公开(公告)号：US08740137B2
公开(公告)日：2014-06-03
申请号：US12443913
申请日：2007-10-02
申请人： Guy Bernard Vauchel , Serge Epherre-Iriart
发明人： Guy Bernard Vauchel , Serge Epherre-Iriart
IPC分类号： B64D29/06 , B64D29/08
CPC分类号： F02C7/04 , B64D29/08 , B64D33/02 , B64D2033/0226 , F05D2230/64 , F05D2240/14 , Y02T50/671
摘要： A nacelle for a turban engine includes an air intake structure and a central structure. The central structure has a casing intended to surround a fan and an external structure. The air intake structure has at least one internal panel attached to the central structure via the casing and therewith forming a fixed structure and at least one longitudinal external panel attached removably to the fixed structure and incorporating an air intake lip. The external panel is moveable between an operating position and a maintenance position in which the external panel is separated from the external structure of the central section and the air intake lip is separated from the internal panel of the air intake structure.
摘要翻译：用于头巾发动机的机舱包括进气结构和中央结构。中央结构具有用于围绕风扇和外部结构的壳体。进气结构具有经由壳体连接到中心结构的至少一个内部面板，并且由此形成固定结构，并且至少一个纵向外部面板可拆卸地附接到固定结构并且包括进气口。外部面板可以在操作位置和维护位置之间移动，其中外部面板与中心部分的外部结构分离，并且进气口与进气结构的内部面板分离。

9. 发明授权

US08739552B2 Structural nacelle 失效
标题翻译：结构机舱
公开(公告)号：US08739552B2
公开(公告)日：2014-06-03
申请号：US12302998
申请日：2007-06-11
申请人： Guy Bernard Vauchel , Anne-Laure Gibouin , Regis Fassier , Jean-Philippe Joret , Jerome Collier , Guillaume Lefort , Pierre-Alain Chouard
发明人： Guy Bernard Vauchel , Anne-Laure Gibouin , Regis Fassier , Jean-Philippe Joret , Jerome Collier , Guillaume Lefort , Pierre-Alain Chouard
IPC分类号： F01D25/30 , B64D27/00
CPC分类号： B64D29/00 , B64D27/18
摘要： The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.
摘要翻译：本发明一方面涉及一种用于双流涡轮反应器（2）的机舱（1），其包括前进气部分（5），中间部分（6），用于围绕所述风机涡轮反应器和后部部分（7），所述后部部分具有旨在用作到所述涡轮反应器的后部的壳体的内部结构（7b），其特征在于，所述内部结构具有适于使所述机舱被紧固的附接装置连接到在所述内部结构的至少一部分上连接到飞机的固定结构（13）的塔架（12），另一方面，连接到具有这种机舱的飞行器。

10. 发明授权

US08578698B2 Cascade-type thrust reverser for jet engine 失效
标题翻译：用于喷气发动机的级联式推力反向器
公开(公告)号：US08578698B2
公开(公告)日：2013-11-12
申请号：US12445437
申请日：2007-09-11
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： F02K1/68
CPC分类号： F02K1/72
摘要： A fan duct (5) is defined between an inner skin (2) and an outer skin into which the inner skin of the sliding cover (7) is incorporated in the direct-thrust configuration. The inner skin of the sliding cover (7) comprises an annular part extending radially inwards and capable, in the reverse-thrust configuration, of coming to face a larger-diameter annular part of the inner skin (2) of the fan duct (5). The annular part of the sliding cover (7) comprises at least one flap (8) mounted such that it can pivot between the retracted position and a deployed position in which a front part (8a) of the flap (8), upstream of its middle axis (9) about which it is articulated, projects into the fan duct (5). Translational stop means (11) are provided in order, in the reverse thrust position, to act on a rear part (8b) of the flap (8) in such a way as to cause the flap (8) to pivot into the deployed position to close off the fan duct (5).
摘要翻译：风扇导管（5）被限定在内表皮（2）和滑动盖（7）的内表皮以直推式构成的外皮之间。滑盖（7）的内表面包括径向向内延伸的环形部分，并且能够以反向推力构型面对风扇导管（5）的内表皮（2）的较大直径的环形部分）。滑动盖（7）的环形部分包括至少一个翼片（8），其安装成使得其能够在缩回位置和展开位置之间枢转，在该展开位置中，翼片（8）的前部（8a）中间轴（9）围绕其铰接，突出到风扇导管（5）中。平移止动装置（11）以反推力位置的顺序设置成作用在挡板（8）的后部（8b）上，以使挡板（8）枢转到展开位置关闭风扇导管（5）。

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