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1.发明授权Thrust inverter with translatable cascade vanes having detachable front frame 有权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
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。
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2.发明授权Strut designed to support an aircraft turbojet engine, and nacelle comprising such a strut 有权支架设计用于支撑飞机涡轮喷气发动机，以及包括这种支柱的机舱公开(公告)号：US08840061B2
公开(公告)日：2014-09-23
申请号：US13121470
申请日：2009-08-05
申请人： Pierre Caruel , Guy Bernard Vauchel
发明人： Pierre Caruel , Guy Bernard Vauchel
CPC分类号： B64D27/26 , B64D29/08 , F02C7/20 , F05D2250/70 , F05D2260/50 , Y02T50/44 , Y02T50/672
摘要： This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.
摘要翻译： 一个用于支撑飞机涡轮喷气发动机的支柱（9）一方面具有用于在风扇（3）的壳体（1）或气体发生器（5）的壳体之间连接的连接部分（11） ）所述涡轮喷气发动机和所述飞行器的机翼，另一方面是固定到所述连接部分（11）并被设计成形成所述飞行器的上部的Y形箱形部分（19） 所述机舱的内部固定结构。
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公开(公告)号：US20120217320A1
公开(公告)日：2012-08-30
申请号：US13510352
申请日：2010-10-26
IPC分类号： B63H11/10
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： The present invention relates to a thrust inverter for a turbojet engine nacelle (1) including at least one outer cowl (11) that is movable between a closed position and a thrust inversion position, said movable cowl also being able to be opened into a supporting position towards which said movable cowl is hinged and guided through the use of a guiding means that is suitable to said movable cowl and located substantially on a pylon, to which the nacelle is intended to be attached and at least one front frame (15) capable of being mounted downstream from an air blower housing for said turbojet engine and directly or indirectly holds at least one flow diversion means (12). Said thrust inverter is characterized in that the front frame is detachably connected to the housing in a translatable manner along at least one related guiding member (17) once said front frame is detached from the housing.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机机舱（1）的推力逆变器，其包括至少一个能够在关闭位置和推力倒置位置之间移动的外罩（11），所述可动罩也能够被打开成支撑 所述可移动整流罩铰接并引导通过使用适于所述可移动整流罩并且基本上位于所述机舱旨在附接的塔架上的导向装置的位置，以及至少一个前框架（15）能够 被安装在用于所述涡轮喷气发动机的鼓风机壳体的下游，并且直接或间接保持至少一个分流装置（12）。 所述推力逆变器的特征在于，一旦所述前框架与壳体分离，前框架可沿着至少一个相关的引导构件（17）以可平移的方式可拆卸地连接到壳体。
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公开(公告)号：US20110284660A1
公开(公告)日：2011-11-24
申请号：US13131292
申请日：2009-11-23
申请人： Guy Bernard Vauchel , Pierre Caruel
发明人： Guy Bernard Vauchel , Pierre Caruel
IPC分类号： F02K1/62
CPC分类号： F02K1/763 , F05D2220/36
摘要： The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion (15) downstream from which is mounted at least one cowl (9) movable between a direct-jet position, in which the cowl (9) is aligned with the stationary portion (15), and a thrust-reversal position, in which the mobile cowl (9) is spaced apart from the stationary portion (15) so as to define an opening for the passage of a secondary flow (F), a means for deflecting (16) the secondary flow (F) through the passage opening, an actuator means (45) and a means (24) for guiding the mobile cowl (9) relative to the stationary portion (15), at least a first and a second adjacent cascade vane (13), positioned at an angle (B) relative to the movement axis (A) of the mobile cowl (9), arranged opposite the passage opening such that the deflected secondary flow (F) at least partially passes through the first and second vanes (13) in order to increase the deflection of said secondary flow (F) in the upstream direction, said actuator means (45) and means (24) for guiding the mobile cowl (9) being arranged between the first and second vanes (13). A covering wall (31) connects said first and second vanes (13), bypassing said actuator means (45) and guiding means (24).
摘要翻译： 本发明涉及一种用于涡轮风扇发动机机舱的推力反向器，其包括固定部分（15），下游安装有至少一个整流罩（9），所述整流罩（9）可在直接喷射位置之间移动，在该喷射位置，整流罩（9） 固定部分（15）和推力反转位置，其中可移动导管（9）与静止部分（15）间隔开，以便限定用于二次流（F）通过的开口， 用于通过通道开口偏转（16）二次流（F），致动器装置（45）和用于相对于固定部分（15）引导可移动导向罩（9）的装置（24），至少第一和 相对于可移动前襟（9）的移动轴线（A）定位成角度（B）的第二相邻级联叶片（13），与所述通道开口相对设置，使得所述偏转的二次流（F）至少部分地通过 通过第一和第二叶片（13），以便增加所述二次流（F）的偏转 所述致动器装置（45）和用于引导布置在第一和第二叶片（13）之间的移动整流罩（9）的装置（24）。 覆盖壁（31）连接所述第一和第二叶片（13），绕过所述致动器装置（45）和引导装置（24）。
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5.发明申请STRUT DESIGNED TO SUPPORT AN AIRCRAFT TURBOJET ENGINE, AND NACELLE COMPRISING SUCH A STRUT 有权STRUT设计用于支持飞机涡轮发动机，以及包含这样的发动机的NACELLE公开(公告)号：US20110174919A1
公开(公告)日：2011-07-21
申请号：US13121470
申请日：2009-08-05
申请人： Pierre Caruel , Guy Bernard Vauchel
发明人： Pierre Caruel , Guy Bernard Vauchel
CPC分类号： B64D27/26 , B64D29/08 , F02C7/20 , F05D2250/70 , F05D2260/50 , Y02T50/44 , Y02T50/672
摘要： This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.
摘要翻译： 一个用于支撑飞机涡轮喷气发动机的支柱（9）一方面具有用于在风扇（3）的壳体（1）或气体发生器（5）的壳体之间连接的连接部分（11） ）所述涡轮喷气发动机和所述飞行器的机翼，另一方面是固定到所述连接部分（11）并被设计成形成所述飞行器的上部的Y形箱形部分（19） 所述机舱的内部固定结构。
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公开(公告)号：US08985508B2
公开(公告)日：2015-03-24
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
CPC分类号： B64D27/26 , B64D29/06 , B64D2027/268 , Y02T50/44
摘要： A suspension assembly for an aircraft turbojet engine includes a pylon and connecting rods for taking up the thrust of the turbojet engine which is connected to the pylon. In particular, the suspension assembly includes an insulator which is separate from the pylon and thermally insulates the connecting rods from the turbojet engine.
摘要翻译： 用于飞机涡轮喷气发动机的悬架组件包括用于承受连接到塔架的涡轮喷气发动机的推力的塔架和连接杆。 特别地，悬架组件包括与塔架分离并将连接杆与涡轮喷气发动机热绝缘的绝缘体。
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公开(公告)号：US20120247571A1
公开(公告)日：2012-10-04
申请号：US13514554
申请日：2010-11-26
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。
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8.发明申请公开(公告)号：US20120228403A1
公开(公告)日：2012-09-13
申请号：US13511279
申请日：2010-11-25
IPC分类号： B64D33/04
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。
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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
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）。
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10.发明授权Assembly for an aircraft turbojet engine comprising a thrust reversal cowl 有权用于包括推力反转罩的飞行器涡轮喷气发动机的组装公开(公告)号：US09249756B2
公开(公告)日：2016-02-02
申请号：US13511279
申请日：2010-11-25
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 characterized 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。
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