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61. 发明授权

US08820344B2 Turbojet engine nacelle 有权
标题翻译：涡轮喷气发动机舱
公开(公告)号：US08820344B2
公开(公告)日：2014-09-02
申请号：US13145705
申请日：2010-02-01
申请人： Guy Bernard Vauchel , Stephane Beilliard
发明人： Guy Bernard Vauchel , Stephane Beilliard
IPC分类号： F02C7/042 , B64D29/06 , F02C7/04 , B64D33/02
CPC分类号： F02C7/04 , B64D29/06 , B64D33/02 , B64D2033/0286 , F05D2240/14 , F05D2250/41 , Y02T50/671 , Y10T137/0536 , Y10T137/0645
摘要： The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside. In addition, the outer structure is equipped with at least one reinforcing beam (10) designed to transmit loads between the annular lip (7) and the cowl (9), said beam (10) extending in the radial plane (P) of the air inlet from the outer structure towards the inner structure and comprising guide means (17) capable of co-operating with complementary guide means (23) belonging to the inner structure. The guide means (17) of the beam (10) and the complementary guide means (23) of the inner structure are offset with respect to the radial plane (P) in which the beam (10) extends.
摘要翻译：本发明涉及涡轮喷气发动机机舱（1），其包括：外部结构，其包括限定空气入口的环形凸缘和作为所述环形唇缘的延续部延伸的整流罩（9），以及内部固定结构（19），其作为继续进气口，并包括配备有至少一件需要维护或监控的设备的区域。上述外部结构可以在整流罩（9）覆盖配备有设备的区域的操作位置与罩（9）显露所述区域的维护位置之间相对于内部结构移动，以便允许进入设备从外面。另外，外部结构配备有至少一个加强梁（10），其被设计成在环形唇缘（7）和整流罩（9）之间传递载荷，所述梁（10）在径向平面（P）中延伸空气入口从外部结构朝向内部结构并且包括能够与属于内部结构的互补引导装置（23）协作的引导装置（17）。梁（10）的引导装置（17）和内部结构的互补引导装置（23）相对于梁（10）延伸的径向平面（P）偏移。

62. 发明授权

US08793973B2 Thrust reverser for a dual-flow turbine engine nacelle 有权
标题翻译：双流涡轮发动机舱的推力反向器
公开(公告)号：US08793973B2
公开(公告)日：2014-08-05
申请号：US13320984
申请日：2010-05-18
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： F02K3/02 , F02K1/00 , B63H11/10 , B63H25/46 , B05B12/00 , F02K1/76 , F02K1/72
CPC分类号： F02K1/72 , F02K1/763 , F05D2270/66 , Y02T50/671
摘要： The invention relates to a thrust reverser (1) for the nacelle of a dual-flow turbine engine, in which the bypass means (4) and the actuation jacks (22) of the sliding cowling (2) and of the reverse flaps (20) are arranged in two substantially parallel planes arranged above one another in the radial direction of the nacelle. The invention also relates to a nacelle for a dual-flow turbine engine that comprises such a thrust reverser.
摘要翻译：本发明涉及一种用于双流涡轮发动机的机舱的推力反向器（1），其中所述旁通装置（4）和所述滑动罩（2）和所述反向翼片（20）的致动插座（22））布置在沿机舱的径向相互布置的两个基本上平行的平面中。本发明还涉及一种用于双流涡轮发动机的机舱，其包括这种推力反向器。

63. 发明申请

US20120247571A1 JET ENGINE NACELLE REAR ASSEMBLY 审中-公开
标题翻译：喷气机发动机零件组件
公开(公告)号：US20120247571A1
公开(公告)日：2012-10-04
申请号：US13514554
申请日：2010-11-26
申请人： Guy Bernard Vauchel , Pierre Caruel , Jean-Philippe Joret
发明人： Guy Bernard Vauchel , Pierre Caruel , Jean-Philippe Joret
IPC分类号： F02B77/00
CPC分类号： B64D29/06 , B64D29/08 , F01D25/243 , F02K1/80 , Y10T137/0536
摘要： The present invention relates to a nacelle rear assembly (1) including a pod-shaped internal structure (11), said internal structure comprising at least one downstream portion (15) and one upstream portion (13) that are each movably mounted between an operative position, in which said portions are connected, and at least one maintenance position, in which said portions are separate from each other, the downstream portion being movably mounted by means of sliding while the upstream portion is movable by opening at least one door. The downstream portion and upstream portion are provided with a connection means that is capable of engaging therebetween. Said assembly is characterized in that at least one of the downstream and upstream portions is provided with a hinging means (131, 151) having a range of movement in at least one direction so as to enable stress-free control and operation of the portion in question.
摘要翻译：本发明涉及一种包括荚状内部结构（11）的机舱后部组件（1），所述内部结构包括至少一个下游部分（15）和一个上游部分（13），每个下游部分（15）和一个上游部分（13）位置，其中所述部分被连接，以及至少一个维护位置，其中所述部分彼此分离，所述下游部分通过滑动可移动地安装，同时上游部分通过打开至少一个门而可移动。下游部分和上游部分设置有能够在其间接合的连接装置。所述组件的特征在于，所述下游部分和上游部分中的至少一个设置有铰链装置（131,151），所述铰接装置具有在至少一个方向上的运动范围，以便能够对所述部分进行无应力控制和操作题。

64. 发明申请

US20120228403A1 ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE COMPRISING A THRUST REVERSAL COWL 有权
标题翻译：用于包含反转轮的飞机涡轮发动机的组装
公开(公告)号：US20120228403A1
公开(公告)日：2012-09-13
申请号：US13511279
申请日：2010-11-25
申请人： Pierre Caruel , Guy Bernard Vauchel , Jean-Philippe Joret , Andre Baillard
发明人： Pierre Caruel , Guy Bernard Vauchel , Jean-Philippe Joret , Andre Baillard
IPC分类号： B64D33/04
CPC分类号： F02K1/766 , B64D29/06 , F02K1/72
摘要： The invention relates to an assembly for a turbojet engine which includes a pylon (1) and a nacelle supported by said pylon (1). Said nacelle (3) includes a grid thrust reverser (21) including an integral cowl mounted so as to slide on rails (15), which are arranged on both sides of said pylon (1), between a direct jet position and a thrust reversal position. Said assembly is characterised in that it includes means (23, 31) for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon (1) and the cowl.
摘要翻译：本发明涉及一种用于涡轮喷气发动机的组件，其包括塔架（1）和由所述塔架（1）支撑的机舱。所述机舱（3）包括格栅推力反向器（21），其包括安装成在所述塔架（1）的两侧上的导轨（15）之间在直接喷射位置和推力反向位置。所述组件的特征在于它包括用于阻挡整流罩在轨道（15）上的滑动运动的装置（23,31），所述装置插入在塔架（1）和整流罩之间。

65. 发明申请

US20120160933A1 STRUCTURING ASSEMBLY FOR AN EXHAUST NOZZLE 审中-公开
标题翻译：用于排气喷嘴的结构装配
公开(公告)号：US20120160933A1
公开(公告)日：2012-06-28
申请号：US13394250
申请日：2010-08-31
申请人： Guy Bernard Vauchel , Eric Conete
发明人： Guy Bernard Vauchel , Eric Conete
IPC分类号： F02K1/44
CPC分类号： F02K1/827 , F05D2250/283 , F05D2300/603 , Y02T50/672
摘要： The invention relates to a structuring assembly (13) for an exhaust nozzle, including the following main elements: (a) an outer skin (22) including a non-acoustic portion (33); (b) an inner structuring skin (23); (c) an acoustic structure (21) including cells (27) having a cellular core, said acoustic structure being arranged between the outer skin (22) and the inner structuring skin (23), at least one of said main elements being made of a composite material, and the acoustic structure (21) being supported between the outer skin (22) and inner structuring skin (23) by linking means (31; 41) attached to the inner structuring skin (23) and to the non-acoustic portion (33) of the outer skin (22) so as to transfer the stresses onto the inner structuring skin (23) and the non-acoustic portion (33) of the outer skin (22). The invention also relates to an exhaust nozzle for a nacelle, comprising such a structuring assembly (13), as well as to a nacelle.
摘要翻译：本发明涉及一种用于排气喷嘴的结构组件（13），其包括以下主要元件：（a）包括非声部分（33）的外皮（22）; （b）内部构造皮肤（23）; （c）包括具有多孔芯的电池（27）的声学结构（21），所述声学结构布置在外皮（22）和内结构皮肤（23）之间，所述主要元件中的至少一个由复合材料，并且通过连接到内部结构化皮肤（23）上的连接装置（31; 41）和与非内部构造皮肤（23）连接的外壳（22）和内部结构皮肤（23）之间的声学结构（21）（22）的部分（33），以将应力转移到外皮（22）的内结构皮肤（23）和非声部（33）上。本发明还涉及一种用于机舱的排气喷嘴，其包括这种结构组件（13）以及机舱。

66. 发明授权

US08070101B2 Locking system for a movable nacelle cowl 有权
标题翻译：可移动机舱罩的锁定系统
公开(公告)号：US08070101B2
公开(公告)日：2011-12-06
申请号：US12439017
申请日：2007-07-02
申请人： Guy Bernard Vauchel , Georges Alain Bouret
发明人： Guy Bernard Vauchel , Georges Alain Bouret
IPC分类号： B64C1/14
CPC分类号： B64D29/06 , Y10T292/699
摘要： The present invention relates to a locking system (20) for a movable lateral cowl (8) of a turbine engine nacelle intended to be connected to a pylon (4) of an aircraft, comprising, on the one hand, a clevis (21) intended to be connected to the pylon, and, on the other hand, a rod (22) intended to be mounted on the movable cowl and capable of engaging with the clevis when the movable cowl is in the closed position, characterized in that the rod is mounted so that it can move translationally along a substantially longitudinal axis of the movable cowl so as to form a slider which can shift between a locked position, in which it is engaged with the clevis and provides a structural connection between the pylon and the movable cowl, and an unlocked position, in which it is disengaged from the clevis and allows the movable cowl to be opened.
摘要翻译：本发明涉及一种用于涡轮发动机机舱的可移动侧向罩（8）的锁定系统（20），其旨在连接到飞机的塔架（4），一方面包括一个U形夹（21），意图是连接到塔架，另一方面是一个杆（22），用于安装在可移动的整流罩上，并且当可移动整流罩处于关闭位置时能够与U形夹相接合，其特征在于，杆被安装成使得其可以沿着可移动整流罩的基本上纵向的轴线平移地移动，以便形成滑块，该滑块可以在锁定位置之间移动，在该位置中，滑块与锁定位置相接合，并且提供在塔架和可移动的支架之间的结构连接整流罩和解锁位置，其中它与U形夹脱离，并允许可动罩被打开。

67. 发明申请

US20110284686A1 SUSPENSION ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE 有权
标题翻译：航空器涡轮发动机悬架总成
公开(公告)号：US20110284686A1
公开(公告)日：2011-11-24
申请号：US13146211
申请日：2010-01-21
申请人： Pierre Caruel , Guy Bernard Vauchel
发明人： Pierre Caruel , Guy Bernard Vauchel
IPC分类号： B64D27/10 , B64D29/06 , B64D29/00 , B64D27/26 , B64C1/40
CPC分类号： B64D27/26 , B64D29/06 , B64D2027/268 , Y02T50/44
摘要： The invention relates to a suspension assembly for an aircraft turbojet engine (3), including a pylon (1) up and connected to the pylon (1), and connecting rods (13a, 13b) for taking up the thrust of the turbojet engine (3) remarkable in that the assembly includes means (19a, 19b; 25) separate from said pylon for thermally insulating the connecting rods (13a, 13b) from the turbojet engine (3).
摘要翻译：本发明涉及一种用于飞行器涡轮喷气发动机（3）的悬挂组件，其包括上升并连接到塔架（1）的塔架（1）和连接杆（13a，13b），用于承受涡轮喷气发动机的推力 3）显着的是，组件包括与所述塔架分离的用于将连接杆（13a，13b）与涡轮喷气发动机（3）进行绝热的装置（19a，19b; 25）。

68. 发明申请

US20110240137A1 OVERPRESSURE HATCH INTENDED TO BE MOUNTED ON A WALL OF A TURBOJET ENGINE NACELLE 审中-公开
标题翻译：预计将安装在一个涡轮发动机舱上的过压保护罩
公开(公告)号：US20110240137A1
公开(公告)日：2011-10-06
申请号：US13132677
申请日：2009-11-18
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： B64D29/00
CPC分类号： B64D29/00 , Y10T137/0645
摘要： The invention relates to an overpressure hatch (21) intended to be mounted on a wall (23) of a nacelle (1) for a turbojet engine (5), the overpressure hatch (21) comprising a support (22) intended to be fixed to the wall (23), and at least one discharge element (25) able to move with respect to said support (22), said hatch (21) comprising at least one part (27) of lower mechanical strength than the remainder of the overpressure hatch (21) so that air at an overpressure inside the nacelle (1) can be discharged when the internal pressure applied to said hatch (21) more or less reaches a threshold pressure level lower than the maximum pressure that the nacelle structure can withstand. The invention also relates to a turbojet engine nacelle comprising at least one hatch (21) according to the invention.
摘要翻译：本发明涉及一种旨在安装在用于涡轮喷气发动机（5）的机舱（1）的壁（23）上的超压舱口（21），该超压舱口（21）包括一个用于固定的支撑件（22）至少一个能够相对于所述支撑件移动的排放元件（25），所述舱口（21）包括至少一个部分（27），所述至少一个部分（27）的机械强度比其余部分超压舱口（21），使得当施加到所述舱口（21）的内部压力或多或少达到低于机舱结构能够承受的最大压力的阈值压力水平时，机舱（1）内部的超压下的空气可以排出。本发明还涉及包括根据本发明的至少一个舱口（21）的涡轮喷气发动机机舱。

69. 发明申请

US20110131945A1 ASSEMBLY OF COMPONENTS CONNECTED BY A DEVICE THAT MAINTAINS THE INTEGRITY OF THE SURFACE OF ONE OF THE COMPONENTS 有权
标题翻译：组装与保持组成部分之一的完整性的设备连接的组件
公开(公告)号：US20110131945A1
公开(公告)日：2011-06-09
申请号：US13056727
申请日：2009-07-28
申请人： Guy Bernard Vauchel , Guillaume Ruckert
发明人： Guy Bernard Vauchel , Guillaume Ruckert
IPC分类号： F02G3/00 , B32B3/26 , B32B5/02 , B32B5/24 , B32B5/18 , B32B3/10 , B32B7/12 , B32B3/12
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286 , F02C7/045 , F02C7/047 , F05D2260/96 , Y02T50/672 , Y10T137/0536 , Y10T428/12479 , Y10T428/24149 , Y10T428/24322 , Y10T428/249953 , Y10T428/24997 , Y10T428/249976 , Y10T428/249982 , Y10T442/59
摘要： This assembly comprises a first component (9), a second component (3), and a connecting device (19) for connecting these two components together, this device (19) being of the type that maintains the integrity of the surface of said second component (3), and the assembly being noteworthy in that said connecting device (19) comprises a structural skin (21) fixed to said first component (9) and a porous material (23) attached to this structural skin and fixed by contact to said second component (3).
摘要翻译：该组件包括第一部件（9），第二部件（3）和用于将这两个部件连接在一起的连接装置（19），该装置（19）是保持所述第二部件组件（3），并且组件是值得注意的，因为所述连接装置（19）包括固定到所述第一部件（9）的结构皮肤（21）和附接到该结构皮肤上的多孔材料（23），并通过接触固定所述第二组分（3）。

70. 发明申请

US20110120076A1 STRUCTURE FOR AN AIR INLET LIP OF AN ELECTRIC DE-ICING POD COMPRISING AN ACOUSTIC ATTENUATION ZONE 有权
标题翻译：用于包含声音衰减区域的电动灭蚊器的空气入口结构
公开(公告)号：US20110120076A1
公开(公告)日：2011-05-26
申请号：US12161194
申请日：2007-03-08
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： F02C7/047
CPC分类号： B64D15/12 , B64D33/02 , B64D2033/0233 , F02C7/047 , H05B3/267 , Y02T50/672
摘要： The present invention relates to a structure (7) for a lip (4a) of an air inlet (4) of a turbojet pod (1) comprising an outer skin (12), designed to be oriented towards the outside of the lip, and an inner skin (13), designed to be oriented towards the inside of the lip, characterized in that it comprises at least one electric heating element (14) situated between the inner skin and the outer skin and capable of being connected to electric supply means (15, 16), at least one electric heating element extending at least partly through an acoustic attenuation zone having perforations (11) passing through the structure and associated with an acoustic attenuation structure (30) fitted to the inner skin.
摘要翻译：本发明涉及一种用于涡轮喷气发动机舱（1）的空气入口（4）的唇缘（4a）的结构（7），其包括设计成面向唇部外侧的外皮（12），以及设计成朝向唇部内侧的内皮（13），其特征在于，其包括至少一个位于内表皮和外皮之间的电加热元件（14），并且能够连接到电源装置（15,16），至少一个电加热元件至少部分地延伸穿过穿过所述结构的穿孔（11）的声学衰减区域，并且与安装到内部皮肤上的声学衰减结构（30）相关联。

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