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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。

3. 发明申请

US20080315033A1 Turbojet Engine Mounting Structure For Aircraft 有权
标题翻译：飞机喷气发动机安装结构
公开(公告)号：US20080315033A1
公开(公告)日：2008-12-25
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： B64D27/00
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。

4. 发明申请

US20080272230A1 Engine Assembly for Aircraft 有权
标题翻译：飞机发动机总成
公开(公告)号：US20080272230A1
公开(公告)日：2008-11-06
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。

5. 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。

6. 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。

7. 发明申请

US20120070287A1 PROPELLER FOR AN AIRCRAFT TURBINE ENGINE COMPRISING A VANE RETAINING RING MOUNTED ABOUT THE HUB 有权
标题翻译：用于航空器涡轮发动机，包括关于集线器的VANE保持环
公开(公告)号：US20120070287A1
公开(公告)日：2012-03-22
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： F01D5/30
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。

8. 发明授权

US07445179B2 Engine assembly for aircraft 有权
标题翻译：飞机发动机总成
公开(公告)号：US07445179B2
公开(公告)日：2008-11-04
申请号：US11527622
申请日：2006-09-27
申请人： Lionel Diochon , Frederic Journade , Laurent LaFont , Mickael Sarrato , Alain Razafindrabe
发明人： Lionel Diochon , Frederic Journade , Laurent LaFont , Mickael Sarrato , Alain Razafindrabe
IPC分类号： B64D29/00
CPC分类号： B64D27/26 , B64D2027/268
摘要： The invention relates to an engine suspension pylon for an aircraft including a rigid structure provided with a box (24), this pylon also including an engine aft attachment (8) provided with an attachment body (38), and a thrust resistance device (9) generated by the engine. The rigid structure according to the invention includes an offset rib (35) for the attachment body (38), this rib (35) being mounted fixed on the box (24) between the box and the engine (2) and carrying the attachment body. Furthermore, the device (9) includes a thrust resistance spar (9b) of which the forward end is mounted fixed on the rib (35), and the aft end is mounted fixed on the box.
摘要翻译：本发明涉及一种用于飞行器的发动机悬挂塔，其包括设置有箱体（24）的刚性结构，该塔架还包括设置有附接体（38）的发动机后部附件（8）和推力阻力装置（9））。根据本发明的刚性结构包括用于附接体（38）的偏移肋（35），该肋（35）固定在箱体和发动机（2）之间的箱体（24）上并承载附着体。此外，装置（9）包括固定在肋（35）上的前端安装的推力阻力梁（9b），后端安装在箱体上。

9. 发明申请

US20070069069A1 Engine assembly for aircraft 有权
标题翻译：飞机发动机总成
公开(公告)号：US20070069069A1
公开(公告)日：2007-03-29
申请号：US11527622
申请日：2006-09-27
申请人： Lionel Diochon , Frederic Journade , Laurent LaFont , Mickael Sarrato , Alain Razafindrabe
发明人： Lionel Diochon , Frederic Journade , Laurent LaFont , Mickael Sarrato , Alain Razafindrabe
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/268
摘要： The invention relates to an engine suspension pylon for an aircraft including a rigid structure provided with a box (24), this pylon also including an engine aft attachment (8) provided with an attachment body (38), and a thrust resistance device (9) generated by the engine. The rigid structure according to the invention includes an offset rib (35) for the attachment body (38), this rib (35) being mounted fixed on the box (24) between the box and the engine (2) and carrying the attachment body. Furthermore, the device (9) includes a thrust resistance spar (9b) of which the forward end is mounted fixed on the rib (35), and the aft end is mounted fixed on the box.
摘要翻译：本发明涉及一种用于飞行器的发动机悬挂塔，其包括设置有箱体（24）的刚性结构，该塔架还包括设置有附接体（38）的发动机后部附件（8）和推力阻力装置（9））。根据本发明的刚性结构包括用于附接体（38）的偏移肋（35），该肋（35）固定在箱体和发动机（2）之间的箱体（24）上并承载附着体。此外，装置（9）包括固定在肋（35）上的前端安装的推力阻力梁（9b），后端安装在箱体上。

10. 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。

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