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61. 发明授权

US5987881A Thrust reverser door with spring biased movable external panel 失效
标题翻译：推力反向门带弹簧偏置可动外部面板
公开(公告)号：US5987881A
公开(公告)日：1999-11-23
申请号：US041767
申请日：1998-03-13
申请人： Patrick Gonidec , Pascal Gerard Rouyer , Guy Bernard Vauchel
发明人： Patrick Gonidec , Pascal Gerard Rouyer , Guy Bernard Vauchel
IPC分类号： B64D33/00 , F02K1/70
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。

62. 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。

63. 发明授权

US08959768B2 Method for making deicing system on a nacelle panel 有权
标题翻译：在机舱面板上制作除冰系统的方法
公开(公告)号：US08959768B2
公开(公告)日：2015-02-24
申请号：US13057500
申请日：2009-06-02
申请人： Guy Bernard Vauchel , Marc Gerome , Laurence Lemains
发明人： Guy Bernard Vauchel , Marc Gerome , Laurence Lemains
IPC分类号： B21K25/00 , B64D15/12 , F02C7/045 , B64D29/00 , B64D33/02 , F02C7/047 , H05B3/28
CPC分类号： F02C7/045 , B64D29/00 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286 , F02C7/047 , F05D2250/191 , F05D2250/283 , H05B3/28 , Y02T50/67 , Y02T50/672 , Y10T29/49083 , Y10T29/4932 , Y10T29/49622 , Y10T29/49888
摘要： The invention relates to a method for making a deicing system on a panel (22) of a nacelle comprising an outer skin (24) having at least one hole and an inner skin (26), characterized in that it comprises the following steps: A. a grid of resistive elements is positioned on the outer skin (24) with respect to the hole(s) by a positioning means; B. the grid of resistive elements is applied by an application means to the location determined in step A to form the deicing system; C. a surface coating is applied to the resulting deicing system. The present invention also relates to an air inlet lip and to a nacelle comprising a deicing system produced by such method.
摘要翻译：本发明涉及一种在包括具有至少一个孔和内皮（26）的外皮（24）的机舱的面板（22）上制造除冰系统的方法，其特征在于包括以下步骤：A 电阻元件格栅通过定位装置相对于孔定位在外表皮（24）上; B.电阻元件的栅格通过施加装置施加到在步骤A中确定的位置以形成除冰系统; C.对所形成的除冰系统施加表面涂层。本发明还涉及一种进气口和一个包括通过这种方法生产的除冰系统的机舱。

64. 发明授权

US08800258B2 Air intake structure to be mounted upstream of a nacelle middle structure for aircraft engine, and nacelle equipped with such air intake structure 有权
标题翻译：用于飞机发动机的机舱中间结构上游的进气结构和配备有这种进气结构的机舱
公开(公告)号：US08800258B2
公开(公告)日：2014-08-12
申请号：US12681994
申请日：2008-08-28
申请人： Guy Bernard Vauchel , Stephane Beilliard , Jean-Philippe Dauguet
发明人： Guy Bernard Vauchel , Stephane Beilliard , Jean-Philippe Dauguet
IPC分类号： F02G3/00 , F02C7/20 , B64D33/02 , F02C7/047 , B64D15/04
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0233 , F02C7/047 , Y02T50/671
摘要： An air intake structure is mounted upstream of a mid-structure of a nacelle for an aircraft engine. The air intake structure includes an external wall incorporating a lip, a partition defining a deicing compartment in the lip, a deicing manifold extending in the compartment, and a duct for supplying hot air to the deicing manifold. In particular, the external wall is mounted movably with respect to the mid-structure between a rear position and a front position, and the duct is connected in a fixed manner to the mid-structure. The partition is fixed in a sealed manner inside the lip, and the duct is connected to the manifold by a disconnectable seal which is situated in an immediate vicinity of the partition.
摘要翻译：进气结构安装在用于飞行器发动机的机舱的中间结构的上游。进气结构包括外壁，其包括唇缘，在唇缘中限定除冰室的隔板，在隔室中延伸的除冰歧管以及用于向除冰歧管供应热空气的管道。特别地，外壁相对于后部位置和前部位置之间的中间结构可移动地安装，并且管道以固定的方式连接到中间结构。分隔件以密封的方式固定在唇部内部，并且管道通过位于分隔件紧邻处的可断开的密封件连接到歧管。

65. 发明授权

US08668441B2 Deformable structural framework for a turbofan nacelle 失效
标题翻译：涡轮风机舱的可变形结构框架
公开(公告)号：US08668441B2
公开(公告)日：2014-03-11
申请号：US12519088
申请日：2007-10-15
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： B64D29/06 , F02C7/20
CPC分类号： B64D29/08 , B64D2027/264
摘要： The nacelle of the invention includes an air-inlet front section, a middle section for encasing the fan of the turbofan (7) and a rear section including means for connection to a pylon to be connected to the rigid structure or an airplane. The rear section includes a structural framework (18) having at least one aerodynamic smoothing and acoustic panel (21). The acoustic panel (21) is secured on the structural framework (18) by floating or elastic fixation means so that said acoustic panel (21) can be deformed in a direction (31) essentially centrifugal and radial relative to the turbofan (7) in the presence of overpressure air (3) in the engine compartment.
摘要翻译：本发明的机舱包括空气入口前部，用于包封涡扇（7）的风扇的中间部分，以及包括用于连接到要连接到刚性结构或飞机的挂架的装置的后部。后部包括具有至少一个气动平滑和声学面板（21）的结构框架（18）。声学面板（21）通过浮动或弹性固定装置固定在结构框架（18）上，使得所述声学面板（21）可以相对于涡轮风扇（7）基本上离心和径向的方向（31）变形在发动机舱中存在过压空气（3）。

66. 发明授权

US08627644B2 Thrust reverser for a jet engine 有权
标题翻译：用于喷气发动机的推力反向器
公开(公告)号：US08627644B2
公开(公告)日：2014-01-14
申请号：US12531581
申请日：2008-02-20
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： F02K1/72 , F02K1/60
CPC分类号： F02K1/72 , B64D29/08 , F05D2230/80 , F05D2250/42
摘要： The invention relates to a thrust reverser (9) for an aircraft nacelle (1), including: a front frame (11), a cowl (21) which can move between an operating position and an intermediate maintenance position downstream of the front frame (11), means (26) for moving the cowl (21) between closed and open positions, and an inner structure (23) which can move between an operating position and an intermediate maintenance position downstream of the front frame (11). In addition, the cowl (21) comprises two half-cowls (21a, 21b) and the inner structure (23) comprises two structure halves (23a, 23b), whereby said half-cowls (21a, 21b) and said inner structure halves (23a, 23b) can open outward when the cowl (21) and the inner structure (23) are in the intermediate maintenance position.
摘要翻译：本发明涉及一种用于飞机机舱（1）的推力反向器（9），包括：前框架（11），可在前框架下游的操作位置和中间维护位置之间移动的整流罩（21） 11），用于在封闭和打开位置之间移动整流罩（21）的装置（26）和可在前框架（11）下游的操作位置和中间维护位置之间移动的内部结构（23）。另外，整流罩21包括两个半罩（21a，21b），内部结构（23）包括两个结构半部（23a，23b），由此所述半罩（21a，21b）和所述内部结构半部（21）和内部结构（23）处于中间维护位置时，可以向外打开（23a，23b）。

67. 发明授权

US08240982B2 Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone 有权
标题翻译：包括声衰减区的电除冰荚的进气口的结构
公开(公告)号：US08240982B2
公开(公告)日：2012-08-14
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： F01D25/02
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) including 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 includes at least one electric heating element (14) situated between the inner skin and the outer skin and capable of being connected to an electric supply (15, 16), and the 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），该涡轮喷气发动机舱（1）包括被设计为朝向唇部的外侧的外皮（12），以及设计成朝向唇部内侧定向的内表皮（13），其特征在于，其包括位于内皮和外皮之间的至少一个电加热元件（14），并且能够连接到电源（15,16），并且所述至少一个电加热元件至少部分地延伸穿过具有穿过所述结构并且与安装到所述内表皮的声衰减结构（30）相关联的穿孔（11）的声衰减区。

68. 发明申请

US20110192134A1 AIR INTAKE STRUCTURE FOR A TURBINE ENGINE NACELLE 审中-公开
标题翻译：涡轮发动机空气吸入结构
公开(公告)号：US20110192134A1
公开(公告)日：2011-08-11
申请号：US13122888
申请日：2009-07-21
申请人： Guy Bernard Vauchel , Fabien Bravin
发明人： Guy Bernard Vauchel , Fabien Bravin
IPC分类号： F02K3/02
CPC分类号： F02K1/822 , B64D29/06 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F02C7/04 , Y02T50/672 , Y02T50/675
摘要： The invention relates to an air intake structure (4) for a turbine engine nacelle for directing an air flow towards the fan of the turbine engine, said structure comprising at least one outer panel (40), at least one inner panel (41) and an air intake lip (4a) having an inner wall (70) to be in contact with the air flow flowing into the turbine engine and a partition (45) separating the air intake lip (4a) from the rest of the nacelle, the air intake lip (4a) having an extension (60) that can be fastened onto the inner panel (41) and that extends substantially as a continuation of the inner wall (70) towards the downstream side of the air intake structure over a length (I) at least equal to about the maximum distance (d) between the partition (45) and the air intake lip (4a). The invention also relates to a nacelle for a turbine engine comprising such an air intake structure (4).
摘要翻译：本发明涉及一种用于涡轮发动机机舱的进气结构（4），用于将空气流引向涡轮发动机的风扇，所述结构包括至少一个外板（40），至少一个内板（41）和具有与流入涡轮发动机的空气流接触的内壁（70）的进气口（4a）和将进气口（4a）与机舱的其余部分分开的隔板（45），空气进气口（4a）具有能够固定在内板（41）上并且基本上作为内壁（70）的延续部延伸到进气结构的下游侧延伸长度（I）的延伸部（60））至少等于分隔件（45）和进气口（4a）之间的最大距离（d）。本发明还涉及一种用于包括这种进气结构（4）的涡轮发动机的机舱。

69. 发明申请

US20110174899A1 NACELLE WITH A VARIABLE NOZZLE SECTION 有权
标题翻译： NACELLE与可变的喷嘴部分
公开(公告)号：US20110174899A1
公开(公告)日：2011-07-21
申请号：US13120703
申请日：2009-07-10
申请人： Guy Bernard Vauchel
发明人： Guy Bernard Vauchel
IPC分类号： F02K1/54
CPC分类号： F02K1/72 , B64D29/06 , B64D33/04 , F02K1/805 , F05D2300/501 , Y02T50/672
摘要： The invention relates to a nacelle that comprises a fixed structure (20), a nozzle with a variable section, and a cowling (30) mounted on said fixed structure (20) so as to be capable of sliding particularly along a travel so as to modify the section of said nozzle, characterised in that the nacelle further comprises an aerodynamic continuity assembly (40) provided between the fixed structure (20) and the mobile cowling (30), said assembly (40) including an elastic means that can be compressed between the fixed structure and said mobile cowling when the cowling is in the upstream portion of the travel thereof and that can expand when the cowling is in the downstream portion of the travel thereof so as to ensure the aerodynamic continuity of the lines between said fixed structure (20) and said mobile cowling (30).
摘要翻译：本发明涉及一种机舱，其包括固定结构（20），具有可变部分的喷嘴和安装在所述固定结构（20）上的整流罩（30），以便能够特别沿着行进滑动，以便修改所述喷嘴的部分，其特征在于，所述机舱还包括设置在所述固定结构（20）和所述可移动整流罩（30）之间的空气动力学连续性组件（40），所述组件（40）包括可压缩的弹性装置在整流罩处于其行程的上游部分中时，在固定结构和所述可移动整流罩之间，当整流罩位于其行进的下游部分时可以膨胀，以便确保所述固定结构之间的线路的气动连续性（20）和所述移动罩（30）。

70. 发明申请

US20110133025A1 ACOUSTIC ATTENUATION PANEL FOR AIRCRAFT FOR ENGINE NACELLE 有权
标题翻译：用于发动机空调的航空器衰减面板
公开(公告)号：US20110133025A1
公开(公告)日：2011-06-09
申请号：US13056822
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： B64C1/40 , B64D33/02 , B64D15/16
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286 , F02C7/047 , F02C7/24 , F02K1/827 , F05D2300/224 , F05D2300/612 , Y02T50/672
摘要： This acoustic attenuation panel for an aircraft engine nacelle comprises a structuring skin (1) and, by way of acoustic absorption material, a porous material (5) attached to this skin (1).
摘要翻译：用于飞机发动机机舱的声衰减面板包括结构化皮肤（1），并且通过吸声材料，附着到该皮肤（1）上的多孔材料（5）。

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