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1.发明授权公开(公告)号：US07021585B2
公开(公告)日：2006-04-04
申请号：US10874349
申请日：2004-06-24
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： A turbine engine mount to a pylon of an aircraft includes a bracket arranged to be attached to the pylon, and a lever attached in its central part to the bracket via a first connection and two thrust links each joined aft to the lever by a second connection. The lever includes a central part with two arms, and the bracket includes an integral attachment lug placed between the two arms and connected to the arms via a pivot pin to form the first connection. The lever is laterally connected to the bracket via pivot pins passing through the lever and mounted with a clearance to form connections on standby.
摘要翻译： 涡轮发动机安装到飞机的吊架包括布置成附接到塔架的托架和通过第一连接件连接到其托架的杠杆的杠杆和通过第二连接件与杠杆接合的两个推力连杆 。 杠杆包括具有两个臂的中心部分，并且支架包括放置在两个臂之间并且经由枢轴销连接到臂的一体式附接耳，以形成第一连接。 杠杆通过穿过杠杆的枢轴销横向连接到支架，并安装有间隙以形成待机连接。
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2.发明申请公开(公告)号：US20050067528A1
公开(公告)日：2005-03-31
申请号：US10874349
申请日：2004-06-24
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： The present invention pertains to turbine engine mounting onto an aircraft pylon, comprising a bracket (12) arranged to be attached to the pylon, a lever (15;15′) attached in its central part (150;150′) to the bracket by first connection means (150-130) with a pivot pin (136;136′) and two thrust links (20,22; 20′,22′) each joined aft to the lever by second connection means (200-155, 220-157; 200′-155′; 220′-157′) and including engine attachment means at the forward end, characterized in that the first connection means (150-130) consists of two parallel arms (151,153) spaced apart on central part (150) of the lever, cooperating with an attachment lug (130) integral with the bracket via a pivot pin, and lever (15,15′) comprises two third side connection means on standby (155-135, 157-137; 155′-135′; 157′-137′) with bracket (12,12′). The invention provides for simplified mounting with improved safety.
摘要翻译： 本发明涉及安装在飞机吊架上的涡轮发动机，其包括布置成附接到塔架的支架（12），通过下述方式将杆（15; 15'）附接到其中心部分（150; 150'）到托架 具有枢轴销（136; 136'）和两个推力连杆（20,22; 20'，22'）的第一连接装置（150-130），每个通过第二连接装置（200-155,220〜 并且包括位于前端的发动机附接装置，其特征在于，所述第一连接装置（150-130）由在中心部分间隔开的两个平行臂（151,153） 所述杠杆与通过枢轴销与所述支架一体的附接凸耳（130）配合，并且杠杆（15,15'）包括待机（155-135,157-137; 155'）上的两个第三侧连接装置， -135'; 157'-137'）与支架（12,12'）。 本发明提供了简化的安装，改善了安全性。
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公开(公告)号：US20080073461A1
公开(公告)日：2008-03-27
申请号：US11856468
申请日：2007-09-17
申请人： Thibaud GUIBERT , Guillaume Lefort , Marc Tesniere
发明人： Thibaud GUIBERT , Guillaume Lefort , Marc Tesniere
摘要： An integrated propulsive turbojet engine system comprising a downstream cylindrical nacelle structure in two parts, one (26) of which is fixed and comprises a beam (20) for fastening attachment means to the aircraft, and the other (40) of which is able to move between a service position and a maintenance-facilitating open position.
摘要翻译： 一种集成的推进涡轮喷气发动机系统，包括两个部分的下游圆柱形机舱结构，其中一个（26）固定并包括用于将附接装置紧固到飞行器的梁（20），另一个（40）能够 在服务位置和维护便利的打开位置之间移动。
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公开(公告)号：US07108224B2
公开(公告)日：2006-09-19
申请号：US10839133
申请日：2004-05-06
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： A suspension of the turbo fan engine to an aircraft pylon, includes a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking device with a pivot pin. Two thrust rods are each connected by an end to the lever and including at the other end of the fastening device to the engine. The linking device is composed on the central portion of the lever, of two parallel branches apart from one another, and on the fitting, of a central fastening tab, whereas the fastening tab and both branches are held together by dint of the pivot pin.
摘要翻译： 涡轮风扇发动机悬挂在飞机塔架上，包括一个安装在挂架上的配件，一个通过连接装置与枢轴销固定在其中心部分上的杠杆。 两个推力杆各自通过杆的端部连接并且包括在紧固装置的另一端到发动机。 连接装置由杠杆的中心部分组成，两个平行的分支彼此分开，并在配件上组成一个中心紧固片，而紧固片和两个分支则通过枢销固定在一起。
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公开(公告)号：US20070084191A1
公开(公告)日：2007-04-19
申请号：US11426480
申请日：2006-06-26
申请人： Bruno BEUTIN , Marc TESNIERE
发明人： Bruno BEUTIN , Marc TESNIERE
IPC分类号： F02K1/54
CPC分类号： F02K1/766 , F05D2260/52
摘要： The invention relates to thrust reversers comprising at least one mobile element (3), at least one locking device (7) comprising a hook (8) cooperating with a hookable part (6) in order to keep the mobile element (3) in the closed position, and a double detection system (10) detecting closure and locking comprising a sensor (15) for indicating, in particular by a signal, if the mobile element (3) is in the closed position and if the device (7) is in a locked position. According to the invention, the double detection system detecting closure and locking of a mobile element of a turbojet thrust reverser comprises a means (16) of detection of the hookable part (6) and of activation of a second means (17) of detection of the crooked end (13) of the hook (8).
摘要翻译： 本发明涉及包括至少一个移动元件（3），至少一个锁定装置（7）的推力反向器，所述至少一个锁定装置（7）包括与可钩挂部分（6）配合的钩（8），以便将移动元件（3）保持在 以及检测闭合和锁定的双重检测系统（10），包括用于特别地通过信号指示如果移动元件（3）处于关闭位置的传感器（15），并且如果装置（7）是 处于锁定位置。 根据本发明，检测涡轮喷气推进反向器的移动元件的闭合和锁定的双重检测系统包括检测可钩形部件（6）的装置（16）和检测第二装置（17）的第二装置 钩（8）的弯曲端（13）。
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公开(公告)号：US07165743B2
公开(公告)日：2007-01-23
申请号：US10843306
申请日：2004-05-12
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： A front attachment device for attaching an aircraft engine to an aircraft pylon includes an upper brace fitted with elements rigidly fastened to the pylon and first and a second connecting rods, each connected to the engine, via a first ball joint connection at one end portion and to the upper brace via a second ball joint connection on the other end portion. The device further includes in each connecting rod a third stand-by link. The first and second connecting rods are interchangeable with each other.
摘要翻译： 用于将飞行器发动机附接到飞机塔架的前附接装置包括：装配有刚性地固定到塔架上的元件的上支架，以及通过一端部处的第一球窝接头连接到发动机的第一连杆和第二连杆， 通过另一端部分上的第二球形接头连接到上支架。 该装置还包括在每个连接杆中的第三备用连杆。 第一和第二连杆彼此可互换。
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公开(公告)号：US20060219841A1
公开(公告)日：2006-10-05
申请号：US11389260
申请日：2006-03-27
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268 , Y02T50/44
摘要： The present invention relates to a suspension for suspending a jet engine on an aircraft strut, comprising a beam 10 having a platform 11 provided with means for fastening it to the said strut and arranged transversely with respect to the axis of the engine, first 20 and second 40 lateral links each connected by a first pin 21, 41 to the beam 10 and by a second pin 22, 42 to the engine casing, the second lateral link 40 being prolonged in the region of the first pin by a finger 43 housed with clearance in a cavity provided in the beam so as to form a standby safety connection, and a central link 30 arranged between the two lateral links 20, 40 and connected by a first pin 31 to the beam and by a second pin 32 to the said casing. This suspension is characterized in that the beam comprises a clevis 13 for housing the first connecting pin 31 of the central link 30, and the said first pin is distant from the platform 11 so that a space is provided between the platform 11 and the central link 30, this space forming the said cavity in which the finger 43 of the second lateral link 40 is housed with clearance in normal operation. The solution of the invention makes it possible to reduce the weight of the suspension and to simplify the machining thereof.
摘要翻译： 本发明涉及一种用于将喷气发动机悬挂在飞机支柱上的悬架，其包括梁10，其具有平台11，平台11设置有用于将其紧固到所述支柱并相对于发动机的轴线横向布置的装置，第一20和 第二40个横向连杆，每个横向连杆通过第一销钉21,41连接到梁10，第二销钉22,42连接到发动机壳体，第二横向连杆40在第一销的区域中被一个手指43延伸， 在设置在梁中的空腔中的间隙以形成备用安全连接，以及布置在两个横向连杆20,40之间并由第一销31连接到梁的中心连杆30以及通过第二销32连接到所述 套管。 该悬架的特征在于，梁包括用于容纳中心连杆30的第一连接销31的U形夹13，并且所述第一销远离平台11，使得在平台11和中心连杆 如图30所示，形成所述腔的该空间，其中第二侧向连杆40的指状物43在正常操作中被间隙容纳。 本发明的解决方案可以减小悬架的重量并简化其加工。
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公开(公告)号：US06988692B2
公开(公告)日：2006-01-24
申请号：US10838243
申请日：2004-05-05
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： A rear attachment suspension or device of a turbo engine to an aircraft pylon includes an upper brace fitted with a pylon fastening device and hinged by second ball joint connections, first and second rocker bars transversal to the longitudinal axis of the engine on both sides of the axis of the engine and a third rocker bar disposed there between. The rocker bars are linked to the engine by first ball joint connections. The first and second rocker bars each include a third stand-by link and the upper brace is formed of a beam fixed rigidly to the pylon. The rocker bars are designed to ensure their interchangeability, thereby reducing the risks of error during assembly.
摘要翻译： 涡轮发动机到飞机塔架的后附接悬架或装置包括装配有塔架紧固装置并由第二球窝接头连接铰接的上支撑件，第一和第二摇杆在横向于发动机纵向轴线的两侧 发动机的轴线和设置在其间的第三摇杆。 摇杆通过第一球窝接头连接到发动机。 第一和第二摇杆各自包括第三备用连杆，并且上支架由刚性地固定到塔架的梁形成。 摇杆设计用于确保其可互换性，从而降低组装过程中的错误风险。
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公开(公告)号：US20050269445A1
公开(公告)日：2005-12-08
申请号：US11073646
申请日：2005-03-08
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266 , F16C23/10 , F16C2326/43
摘要： The invention pertains to an engine mount onto an aircraft structure comprising at least one connection means between a first and a second element such as an engine case and said structure, characterized by the fact that said connection means comprises an eccentric member housed in a bore of the first element, being rotational about a first axis, the eccentric member comprising a trunnion attached to the second element and of axis off-centred with respect to the first axis of rotation, the eccentric member being rotational about said off-centred axis. The solution of the invention has the advantage of allowing a compact assembly.
摘要翻译： 本发明涉及一种在飞机结构上的发动机支架，其包括在诸如发动机壳体和所述结构的第一和第二元件之间的至少一个连接装置，其特征在于，所述连接装置包括容纳在 所述第一元件围绕第一轴线旋转，所述偏心构件包括附接到所述第二元件的耳轴和相对于所述第一旋转轴线偏心的所述偏心构件，所述偏心构件围绕所述偏心轴线旋转。 本发明的解决方案具有允许紧凑的组装的优点。
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