-
1.发明授权公开(公告)号：US12054273B2
公开(公告)日：2024-08-06
申请号：US18073049
申请日：2022-12-01
发明人： Paolo Messina , Olivier Pautis
摘要： An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.
-
2.发明申请Aircraft nacelle comprising at least one fan cowl door which is mounted so as to be able to rotate about the longitudinal axis of the nacelle 审中-公开飞机机舱包括至少一个风扇整流罩门，其安装成能够围绕机舱的纵向轴线旋转公开(公告)号：US20160340024A1
公开(公告)日：2016-11-24
申请号：US15160579
申请日：2016-05-20
发明人： Olivier Pautis , Jerome Colmagro
CPC分类号： B64C7/02 , B64D27/26 , B64D29/06 , B64D29/08 , F05D2230/72
摘要： A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.
摘要翻译： 具有纵向轴线并且包括底盘的机舱，两个铰接式风扇整流罩门和滑动风扇整流罩门。 每个铰接式风扇整流罩门可旋转地安装在底盘的上部，每个围绕其自身的开口轴线。 开口轴线平行于纵向轴线。 铰接门在关闭位置和打开位置之间枢转。 在其关闭位置的滑动风扇整流罩门被放置在铰接式风扇整流罩门的自由边缘之间。 用于滑动门的滑动装置构造成使得在铰接门的打开位置中，滑动风扇整流罩门可围绕纵向轴线旋转。 机舱具有风扇整流罩门，当处于打开位置时占用更少的空间，并且与没有滑动风扇整流罩门的铰接式风扇罩相比更紧凑。
-
公开(公告)号：US11542022B2
公开(公告)日：2023-01-03
申请号：US16615924
申请日：2017-12-12
发明人： Stéphane Combes , Adeline Soulie , Olivier Pautis
IPC分类号： B64D27/26
摘要： A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.
-
公开(公告)号：US11084597B2
公开(公告)日：2021-08-10
申请号：US16197726
申请日：2018-11-21
发明人： Olivier Pautis , Eric Bouchet , Olivier Barbara
摘要： To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.
-
公开(公告)号：US10550796B2
公开(公告)日：2020-02-04
申请号：US16017634
申请日：2018-06-25
摘要： A turbofan comprising a fan casing and a nacelle comprising a cowl translatable between an advanced position and a pushed-back position in which the mobile cowl and the fan casing define a window therebetween. The nacelle also comprises reverser flaps, each reverser flap being mounted in a linked manner on the mobile assembly between a closed position in which it obstructs the window and an open position in which it does not obstruct the window. The nacelle also has an impelling mechanism comprising a lever arm rotatable on the mobile assembly and having a roller, a connecting rod mounted rotatably between the reverser flap and the lever arm, and a channel receiving the roller, the channel having a front part parallel with the translation direction and a rear part extending after the front part and oriented inward as it progresses from the front toward the rear.
-
公开(公告)号：US10144500B2
公开(公告)日：2018-12-04
申请号：US15160579
申请日：2016-05-20
发明人： Olivier Pautis , Jerome Colmagro
摘要： A nacelle having a longitudinal axis and comprising a chassis, two articulated fan cowl doors and a sliding fan cowl door. Each articulated fan cowl door is rotatably mounted in an upper portion of the chassis, each about their own opening axis. The opening axes are parallel to the longitudinal axis. The articulated doors pivot between a closed position and an open position. The sliding fan cowl door, in its closed position, is placed between free edges of the articulated fan cowl doors. A sliding arrangement for the sliding door is configured such that, in the open position of either articulated door, the sliding fan cowl door can rotate about the longitudinal axis. The nacelle has fan cowl doors which take up less space when in the open position and which are more compact, in comparison to articulated fan cowl doors without a sliding fan cowl door.
-
7.发明申请公开(公告)号：US20170313430A1
公开(公告)日：2017-11-02
申请号：US15496183
申请日：2017-04-25
发明人： Olivier Pautis , Jerome Colmagro , David EWENS
摘要： To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.
-
公开(公告)号：US12129041B2
公开(公告)日：2024-10-29
申请号：US17988862
申请日：2022-11-17
发明人： Olivier Pautis , Jonathan Blanc
CPC分类号： B64D27/40 , F01D25/28 , F02C7/20 , B64D27/16 , B64D27/402
摘要： An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.
-
公开(公告)号：US11713128B2
公开(公告)日：2023-08-01
申请号：US17318454
申请日：2021-05-12
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/268
摘要： An assembly including a connecting device, connecting first and second parts, including first and second links positioned on respective opposite sides of the first and second parts and an interleaved stiffener, positioned between the first and second links, having a first contact face oriented toward the first link and a second contact face oriented toward the second link, parallel to the first face, the first and second contact faces being separated by a distance equal to that separating the first and second links. This interleaved stiffener makes it possible to limit the risks of bending of the links when they are loaded in compression.
-
公开(公告)号：US11679861B2
公开(公告)日：2023-06-20
申请号：US17502417
申请日：2021-10-15
发明人： Paolo Messina , Olivier Pautis
摘要： An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.
-
-
-
-
-
-
-
-
-
搜索结果
26 条记录 (耗时 0.017 秒)
