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1. 发明授权

US08070093B2 Turbojet engine mounting structure for aircraft 有权
标题翻译：用于飞机的Turbojet发动机安装结构
公开(公告)号：US08070093B2
公开(公告)日：2011-12-06
申请号：US12089058
申请日：2006-06-29
申请人： Lionel Diochon , Jean-Michel Cetout , Laurent Lafont , David Chartier
发明人： Lionel Diochon , Jean-Michel Cetout , Laurent Lafont , David Chartier
IPC分类号： B64D27/26
CPC分类号： B64D27/18 , B64D27/26 , B64D2027/264 , Y02T50/44
摘要： A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively.
摘要翻译：飞机涡轮喷气发动机的安装座。安装座包括一个由两个侧板组成的中央箱，该两个侧板通过横向肋条连接，两个侧箱固定在箱体的前部，并设置在其两侧，每个侧箱包括一个后盖框架。形成盒子的肋条之一包括两个侧边延伸部，分别与肋一体成型并分别从盒子的两个侧面板向外突出，两个延伸部分别固定地安装在两个侧盒中的每一个的框架上。

2. 发明申请

US20110192933A1 MAST FOR SECURING AN ENGINE TO AN AIRCRAFT WING 有权
标题翻译：用于将发动机固定在飞机上的MAST
公开(公告)号：US20110192933A1
公开(公告)日：2011-08-11
申请号：US12601650
申请日：2008-05-15
申请人： Bernard Guering , Lionel Diochon
发明人： Bernard Guering , Lionel Diochon
IPC分类号： B64C15/12 , B64D27/26
CPC分类号： B64D27/26 , B64C15/12 , B64D29/02 , Y02T50/44
摘要： A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first eng of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing.
摘要翻译：一种用于将发动机固定到飞机机翼上的固定桅杆，其中所述装置包括两个紧固件，每个紧固件的第一肘板固定到所述发动机上，并且每个紧固件的第二端固定到所述机翼上，其中所述紧固件包括铰链连接装置能够改变上述紧固件的几何形状，以便改变发动机和机翼之间的距离。

3. 发明申请

US20080210811A1 Aircraft Engine Unit 审中-公开
标题翻译：飞机发动机组
公开(公告)号：US20080210811A1
公开(公告)日：2008-09-04
申请号：US11914327
申请日：2006-05-23
申请人： Lionel Diochon , Jean-Michel Cetout , Olivier Teulou
发明人： Lionel Diochon , Jean-Michel Cetout , Olivier Teulou
IPC分类号： B64D27/00
CPC分类号： B64D27/18
摘要： An engine assembly for an aircraft including a turbojet, a suspension pylon, and a plurality of engine suspensions. The plurality of suspensions include a first forward suspension and a second forward suspension fixed to an engine fan case and located symmetrically about a plane defined by a longitudinal axis of the turbojet and its vertical direction, the first and second suspensions each configured to resist forces applied along a longitudinal direction of the turbojet and along its vertical direction. Furthermore, the plurality of suspensions also include an engine aft suspension configured to resist forces applied along the vertical direction.
摘要翻译：一种用于飞行器的发动机组件，包括涡轮喷气发动机，悬架塔架和多个发动机悬架。多个悬架包括第一前悬架和第二前悬架，其固定到发动机风扇壳体并且围绕由涡轮喷气发动机的纵向轴线及其垂直方向限定的平面对称地定位，第一和第二悬架各自构造成抵抗施加的力沿着涡轮喷气发动机的纵向并沿其垂直方向。此外，多个悬架还包括构造成抵抗沿着垂直方向施加的力的发动机后悬架。

4. 发明授权

US08814079B2 Pylon for attaching an aircraft turbine engine comprising aligned front wing ties 有权
标题翻译：用于连接包括对准的前翼缘的飞机涡轮发动机的吊架
公开(公告)号：US08814079B2
公开(公告)日：2014-08-26
申请号：US13205995
申请日：2011-08-09
申请人： Olivier Teulou , Lionel Diochon , Isabelle Petrissans Lloveras
发明人： Olivier Teulou , Lionel Diochon , Isabelle Petrissans Lloveras
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A pylon for attaching a turbine engine of an aircraft having a rigid structure including protruding fittings each having a first orifice and a plurality of ties to attach the pylon onto a wing of the aircraft, the plurality of ties comprising two side front ties to take the thrust forces, the two side front being secured to the first orifices of the protruding fittings to attach the rigid structure firmly to the wing. The plurality of ties further comprises a center front tie positioned between the two side front ties, the center front tie including a ball joint to take forces in a lateral direction of the rigid structure.
摘要翻译：一种用于附接具有刚性结构的飞机的涡轮发动机的塔架，包括突出的接头，每个突出接头均具有第一孔口和多个接头，以将吊架附接到飞行器的机翼上，所述多个连接件包括两个前侧连接件，推力，两侧前端固定在突出配件的第一个孔口上，以将刚性结构牢固地附接到机翼上。所述多个连接件还包括位于所述两个前侧连接件之间的中心前部连接件，所述中间前部连接件包括球形接头，以在所述刚性结构的横向方向上受力。

5. 发明授权

US08579230B2 Attachment pylon for aircraft turboshaft engine, comprising rear flaps with mobile incidence 有权
标题翻译：用于飞机涡轮轴发动机的附件塔，包括具有移动入射的后翼
公开(公告)号：US08579230B2
公开(公告)日：2013-11-12
申请号：US13078460
申请日：2011-04-01
申请人： Lionel Diochon , Steve Bedoin , Damien Prat
发明人： Lionel Diochon , Steve Bedoin , Damien Prat
IPC分类号： B64D27/00 , B64C13/16 , B64C9/00
CPC分类号： B64D29/04
摘要： An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft.
摘要翻译：公开了一种包括具有推进器的涡轮轴发动机和旨在侧向附接在飞行器结构的后部上的附接塔架的飞机发动机组件。塔架具有外表面，其形成具有后缘的空气动力学轮廓，该后缘布置在涡轮轴发动机的螺旋桨的上游。托架包括至少部分地限定后缘的移动后挡板和根据飞行器的入射率的法律来控制翼片的入射的控制器。

6. 发明授权

US08038092B2 Engine assembly for aircraft 有权
标题翻译：飞机发动机总成
公开(公告)号：US08038092B2
公开(公告)日：2011-10-18
申请号：US12088450
申请日：2006-09-26
申请人： Lionel Diochon , Jean-Michel Cetout , Laurent LaFont
发明人： Lionel Diochon , Jean-Michel Cetout , Laurent LaFont
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： An aircraft engine assembly including a turbojet engine, an engine mount, and a plurality of engine attachments. The engine attachments include first and second forward attachments fixed to a fan case and located symmetrically in relation to a plane defined by a longitudinal axis of the turbojet engine and a vertical direction thereof, both forward attachments configured to transfer loads exerted in a longitudinal direction of the turbojet engine and in the vertical direction thereof. Moreover, each of the two forward attachments includes a shear pin mounted on the case and going through two walls of a clevis fixed on the engine mount.
摘要翻译：包括涡轮喷气发动机，发动机支架和多个发动机附件的飞机发动机组件。发动机附件包括固定到风扇壳体并相对于由涡轮喷气发动机的纵向轴线及其垂直方向限定的平面对称地定位的第一和第二前部附件，两个前部附件构造成传递沿纵向方向施加的载荷涡轮喷气发动机和其垂直方向。此外，两个前置附件中的每一个包括安装在壳体上并穿过固定在发动机支架上的U形夹的两个壁的剪切销。

7. 发明申请

US20080216483A1 Engine Assembly for Aircraft Comprising an Engine as Well as a Device for Locking Said Engine 有权
标题翻译：包括发动机的飞机的发动机组件以及用于锁定所述发动机的装置
公开(公告)号：US20080216483A1
公开(公告)日：2008-09-11
申请号：US12064924
申请日：2006-09-22
申请人： Lionel Diochon , Raffaella Mastroberti , Isabelle Petrissans
发明人： Lionel Diochon , Raffaella Mastroberti , Isabelle Petrissans
IPC分类号： F02C7/20 , B64D27/10
CPC分类号： B64D27/26 , B64D2027/264
摘要： An aircraft engine assembly including an engine and a mount device for the engine. The mount device can be positioned between a wing of the aircraft and the engine, and includes a rigid structure and a mechanism to mount the engine on the rigid structure, the mounting mechanism including a first attachment and a second attachment. The first attachment includes two side semi-attachments each fixed to a fan case of the engine, and the second attachment is fixed onto a forward part of a central case of the engine.
摘要翻译：包括发动机和用于发动机的安装装置的飞机发动机组件。安装装置可以位于飞行器的机翼和发动机之间，并且包括刚性结构和将发动机安装在刚性结构上的机构，所述安装机构包括第一附件和第二附件。第一附件包括两个固定在发动机的风扇壳体上的两个侧部附件，第二个附件被固定在发动机中心壳体的前部上。

8. 发明申请

US20070228213A1 Aircraft Engine Unit 有权
标题翻译：飞机发动机组
公开(公告)号：US20070228213A1
公开(公告)日：2007-10-04
申请号：US11571666
申请日：2005-08-01
申请人： Lionel Diochon , Guillaume Seguin
发明人： Lionel Diochon , Guillaume Seguin
IPC分类号： B64D27/16
CPC分类号： B64D27/26 , B64D2027/264
摘要： The invention relates to an engine assembly for an aircraft comprising a turbojet, a engine mount pylon, and a plurality of engine mounts inserted between the engine mount pylon and the turbojet. According to the invention, the plurality of engine mounts comprises a engine mount (6a) designed so as to uniquely resist forces applied along a direction (Y) transverse to the turbojet, this engine mount (6a) comprising an intermediate fitting (46) assembled onto a first fitting (40) fixed to the pylon through two swivel axes (48) oriented parallel along a vertical direction (Z), and a pin (56) oriented along a longitudinal direction (X) and fixed to the intermediate fitting, the pin being installed on a second fitting (58) fixed to the turbojet, with clearance along the longitudinal direction (X).
摘要翻译：本发明涉及一种用于飞行器的发动机组件，其包括涡轮喷气发动机，发动机支架塔和插入在发动机支架塔和涡轮喷气发动机之间的多个发动机支架。根据本发明，多个发动机支架包括设计成独特地抵抗沿横向于涡轮喷气发动机的方向（Y）施加的力的发动机支架（6a），该发动机支架（6a）包括中间配件（46））组装到通过沿着垂直方向（Z）平行定向的两个旋转轴（48）固定到所述塔的第一配件（40）上，以及沿着纵向方向（X）定向并固定到所述中间配件，所述销安装在固定到所述涡轮喷气发动机的第二配件（58）上，沿着所述纵向方向（X）具有间隙。

9. 发明申请

US20070205324A1 Turbojet Pylon for Aircraft 有权
标题翻译：飞机用涡轮喷气塔
公开(公告)号：US20070205324A1
公开(公告)日：2007-09-06
申请号：US11632077
申请日：2005-08-03
申请人： Lionel Diochon , Jerome Durand
发明人： Lionel Diochon , Jerome Durand
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/264
摘要： A turbojet-mounting pylon for an aircraft. The pylon includes a rigid structure including a plurality of arcs arranged so as to jointly delimit a part of a fictitious approximately cylindrical surface with a circular section. The plurality of arcs also includes two lateral thrust resisting arcs located on each side of the central box, each of the two lateral arcs being fixed to each arc in the form of an annular portion, and on each side of the central box.
摘要翻译：用于飞机的涡轮喷气发动机安装塔架。该塔架包括刚性结构，其包括多个弧，其布置成共同限定具有圆形部分的虚构的近似圆柱形表面的一部分。多个弧还包括位于中心箱的每一侧上的两个侧向抗力弧，两个横向弧中的每一个以环形部分的形式并且在中心箱的每一侧固定到每个弧。

10. 发明授权

US09011098B2 Propeller for an aircraft turbine engine comprising a vane retaining ring mounted about the hub 有权
标题翻译：用于飞机涡轮发动机的螺旋桨，包括围绕毂安装的叶片保持环
公开(公告)号：US09011098B2
公开(公告)日：2015-04-21
申请号：US13260130
申请日：2010-04-06
申请人： Laurent Lafont , Damien Prat , Lionel Diochon
发明人： Laurent Lafont , Damien Prat , Lionel Diochon
IPC分类号： B64C11/04 , B64C11/06 , F01D21/04 , F04D29/32
CPC分类号： B64C11/06 , F01D21/045 , F04D29/323 , Y02T50/66 , Y02T50/672
摘要： A propeller for an aircraft turbine engine comprising a plurality of vanes as well as a hub having a plurality of accommodating ports receiving the bases of said vanes, each vane base being rotatably mounted in its associated accommodating port. The propeller also has at least one vane retaining ring structure in the radial direction outwardly from the hub, being cladded around the latter.
摘要翻译：一种用于包括多个叶片的飞行器涡轮发动机的螺旋桨以及具有容纳所述叶片的基部的多个容纳孔的轮毂，每个叶片基座可旋转地安装在其相关联的容纳口中。螺旋桨还具有从轮毂向外径向的至少一个叶片保持环结构，围绕后者包覆。

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