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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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3.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：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：US20120006000A1
公开(公告)日：2012-01-12
申请号：US13257381
申请日：2010-03-09
CPC分类号： F16C7/04 , F02K1/1261 , F02K1/70 , F02K1/72 , F16C7/06 , Y10T74/2142
摘要： The invention relates to a bent connecting rod (31) for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point (35, 38) that are designed so as to enable the pivotal movement of the connecting rod (31) relative to said first and second assemblies, respectively, the bent connecting rod (31) being suitably positionable such that the bend (40) is located upstream from said flow relative to said second pivot point (38), said second pivot point (38) being suitably built into the second movable assembly, characterized in that the bent connecting rod (31) includes at least two portions (33, 37) linked together by at least one self-aligning means (39a, 39b).
摘要翻译： 本发明涉及一种用于将第一组件连接到第二组件的弯曲连接杆（31），所述第二组件可相对于彼此移动，通过该连接杆限定的空间中的流动通过该连接杆。 杆具有至少一个第一和第二枢转点（35,38），其被设计成能够使得连杆（31）相对于所述第一和第二组件分别枢转运动，弯曲的连接杆（31） ）适当地定位，使得弯曲部（40）相对于所述第二枢转点（38）位于所述流动的上游，所述第二枢转点（38）适当地内置在第二可移动组件中，其特征在于，弯曲的连接杆 （31）包括通过至少一个自对准装置（39a，39b）连接在一起的至少两个部分（33,37）。
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公开(公告)号：US20110308257A1
公开(公告)日：2011-12-22
申请号：US12921239
申请日：2009-01-09
IPC分类号： F02C7/20
CPC分类号： B64D27/26 , B64D2027/264
摘要： The present invention relates to an attachment structure (1) for attaching a turbojet engine (2) to a fixed structure of an airplane via an attachment pylon, characterized in that it comprises a one-piece box section intended to extend at least partially on each side of a fan casing (3) of the turbojet engine about a substantially longitudinal axis thereof and comprising, on the one hand, means of attachment to the pylon and, on the other hand, means of attachment of the engine (4) which are positioned on the box section on each side of a substantially longitudinal axis of the turbojet engine and are intended to be connected to part of the turbojet engine in such a way as to react the forces applied thereto.
摘要翻译： 本发明涉及一种用于通过附接塔将涡轮喷气发动机（2）附接到飞机的固定结构的附接结构（1），其特征在于，其包括一个整体的箱部分，其旨在至少部分地延伸到每个 涡轮喷气发动机的风扇壳体（3）的大致纵向轴线的侧面，一方面包括附接到塔架的装置，另一方面，包括附接发动机（4）的装置 定位在涡轮喷气发动机的基本上纵向轴线的每一侧上的箱部分上，并且旨在以与施加到其上的力反应的方式连接到涡轮喷气发动机的一部分。
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公开(公告)号：US09212689B2
公开(公告)日：2015-12-15
申请号：US13257381
申请日：2010-03-09
CPC分类号： F16C7/04 , F02K1/1261 , F02K1/70 , F02K1/72 , F16C7/06 , Y10T74/2142
摘要： The invention relates to a bent connecting rod (31) for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point (35, 38) that are designed so as to enable the pivotal movement of the connecting rod (31) relative to said first and second assemblies, respectively, the bent connecting rod (31) being suitably positionable such that the bend (40) is located upstream from said flow relative to said second pivot point (38), said second pivot point (38) being suitably built into the second movable assembly, characterized in that the bent connecting rod (31) includes at least two portions (33, 37) linked together by at least one self-aligning means (39a, 39b).
摘要翻译： 本发明涉及一种用于将第一组件连接到第二组件的弯曲连接杆（31），所述第二组件可相对于彼此移动，通过该连接杆限定的空间中的流动通过该连接杆。 杆具有至少一个第一和第二枢转点（35,38），其被设计成能够使得连杆（31）相对于所述第一和第二组件分别枢转运动，弯曲的连接杆（31） ）适当地定位，使得弯曲部（40）相对于所述第二枢转点（38）位于所述流动的上游，所述第二枢转点（38）适当地内置在第二可移动组件中，其特征在于，弯曲的连接杆 （31）包括通过至少一个自对准装置（39a，39b）连接在一起的至少两个部分（33,37）。
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公开(公告)号：US20100287910A1
公开(公告)日：2010-11-18
申请号：US12812621
申请日：2008-10-03
摘要： The invention relates to a nacelle (1) that comprises a first cowling (7) and a second cowling (9) capable of covering in particular the area (15) located around the casing of the fan (19) of a turbojet engine (3). The nacelle further includes an intermediate cowling (23) attached to said first cowling (7) so as to sandwich a mast (5) holding said turbojet engine (3). The second cowling (9) is mounted onto the intermediate cowling (23) via removable fastening means.
摘要翻译： 本发明涉及一种机舱（1），其包括能够特别覆盖涡轮喷气发动机（3）的风扇（19）的壳体周围的区域（15）的第一整流罩（7）和第二整流罩（9） ）。 机舱还包括附接到所述第一整流罩（7）的中间整流罩（23），以便夹持固定所述涡轮喷气发动机（3）的桅杆（5）。 第二整流罩（9）通过可移除的紧固装置安装到中间整流罩（23）上。
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公开(公告)号：US20100206981A1
公开(公告)日：2010-08-19
申请号：US12681662
申请日：2008-08-28
申请人： Andre Baillard
发明人： Andre Baillard
IPC分类号： B64D27/18
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： The invention relates to a propulsion assembly for an aircraft, that comprises: a turbojet engine (1) including a fan casing (3) and an engine casing (5); a pylon for holding said turbojet engine (1); and a device for suspending said turbojet engine under the pylon, that comprises two front suspension connecting rods (9), two rear suspension connecting rods (11), and a thrust acceleration connecting rod (15) extending between the front portion (17) of said engine casing (5) and the pylon in a plane containing the axis (A) of said turbojet engine (1). An additional connecting rod (19) extends between said fan casing (3) and said pylon in a direction substantially parallel to that of the axis (A) of said turbojet engine.
摘要翻译： 本发明涉及一种用于飞行器的推进组件，其包括：包括风扇壳体（3）和发动机壳体（5）的涡轮喷气发动机（1）; 用于保持所述涡轮喷气发动机（1）的挂架; 以及用于将所述涡轮喷气发动机悬挂在所述塔架下方的装置，其包括两个前悬挂连杆（9），两个后悬架连杆（11）和推力加速连杆（15），所述推力加速连杆在所述前悬架连杆 所述发动机壳体（5）和所述塔架在包含所述涡轮喷气发动机（1）的轴线（A）的平面内。 附加的连杆（19）在所述风扇壳体（3）和所述塔架之间沿与所述涡轮喷气发动机的轴线（A）基本平行的方向延伸。
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公开(公告)号：US08534597B2
公开(公告)日：2013-09-17
申请号：US12681662
申请日：2008-08-28
申请人： Andre Baillard
发明人： Andre Baillard
IPC分类号： B64D27/10
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： The invention relates to a propulsion assembly for an aircraft, that comprises: a turbojet engine (1) including a fan casing (3) and an engine casing (5); a pylon for holding said turbojet engine (1); and a device for suspending said turbojet engine under the pylon, that comprises two front suspension connecting rods (9), two rear suspension connecting rods (11), and a thrust acceleration connecting rod (15) extending between the front portion (17) of said engine casing (5) and the pylon in a plane containing the axis (A) of said turbojet engine (1). An additional connecting rod (19) extends between said fan casing (3) and said pylon in a direction substantially parallel to that of the axis (A) of said turbojet engine.
摘要翻译： 本发明涉及一种用于飞行器的推进组件，其包括：包括风扇壳体（3）和发动机壳体（5）的涡轮喷气发动机（1）; 用于保持所述涡轮喷气发动机（1）的挂架; 以及用于将所述涡轮喷气发动机悬挂在所述塔架下方的装置，其包括两个前悬挂连杆（9），两个后悬架连杆（11）和推力加速连杆（15），所述推力加速连杆在所述前悬架连杆 所述发动机壳体（5）和所述塔架在包含所述涡轮喷气发动机（1）的轴线（A）的平面内。 附加的连杆（19）在所述风扇壳体（3）和所述塔架之间沿与所述涡轮喷气发动机的轴线（A）基本平行的方向延伸。
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