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    Aircraft cover including means for limiting the scoop phenomena of pneumatic type
    5.
    发明授权
    Aircraft cover including means for limiting the scoop phenomena of pneumatic type 有权
    飞机盖包括用于限制气动式铲斗现象的装置

    公开(公告)号：US09003810B2

    公开(公告)日：2015-04-14

    申请号：US13276495

    申请日：2011-10-19

    申请人： Alain Porte ,  Frederic Chelin ,  Thierry Surply

    发明人： Alain Porte ,  Frederic Chelin ,  Thierry Surply

    IPC分类号： F02C7/20 ,  B64D27/00 ,  B64D29/08 ,  B64D29/06 ,  F01D25/24

    CPC分类号： B64D29/08 ,  B64D29/06 ,  F01D25/24 ,  F02C7/20 ,  Y10T137/0536

    摘要： An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation.

    摘要翻译： 飞机机舱在其外壁处包括相对于机舱可移动的整流罩，以阻止或解除开口。 整流罩包括远离罩的上游边缘的铰接和锁定/解锁元件，其包括用于限制舀出现象的外观的元件。 限制元件包括与机舱的其余部分或分别可以占据锁定状态的整体的至少一个锁，其中锁的一部分与罩或者分别与机舱的其余部分相互干扰并且防止包括径向的变形 整流罩的部件和另一个自由状态，其中部件不再干扰整流罩或分别与机舱的其余部分并且允许罩的打开运动，其中从一个状态到另一个状态的转换由气体压力产生 变异。

    Aircraft nacelle including at least one radial partition between two conducts
    6.
    发明授权
    Aircraft nacelle including at least one radial partition between two conducts 有权
    飞机机舱包括两个导线之间的至少一个径向隔板

    公开(公告)号：US08851416B2

    公开(公告)日：2014-10-07

    申请号：US13270604

    申请日：2011-10-11

    申请人： Alain Porte ,  Jacques Lalane ,  Frederic Chelin ,  Thierry Surply

    发明人： Alain Porte ,  Jacques Lalane ,  Frederic Chelin ,  Thierry Surply

    IPC分类号： F02C7/20 ,  B64D33/02

    CPC分类号： B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  Y10T137/0536

    摘要： An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50′) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52′) that is in contact with the air stream and an edge (54, 54′) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54′)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.

    摘要翻译： 一种飞机机舱，其使得可以沿纵向引导空气流，并且包括沿纵向方向端对端放置的至少两个面板（50,50'），每个面板（50,50'）包括所谓的空气动力学表面（52， 52'）与与所述气流接触的边缘（54,54'）与所述另一面板的边缘接触，其特征在于，至少一个所述面板包括在其边缘（54,54） '） - 至少一个相对于沿着另一个面板的边缘方向延伸的边缘突出的分隔件58，其以与空气动力学表面相切并且包含纵向方向的平面的方式，因此 以限制面板边缘之间的空气循环。

    AIR OUTLET SYSTEM FOR AIRCRAFT LEADING EDGE
    7.
    发明申请
    AIR OUTLET SYSTEM FOR AIRCRAFT LEADING EDGE 有权
    航空飞行器出口边缘系统

    公开(公告)号：US20100327120A1

    公开(公告)日：2010-12-30

    申请号：US12745950

    申请日：2008-12-01

    申请人： Frederic Chelin ,  Thierry Surply ,  Christophe Bourdeau

    发明人： Frederic Chelin ,  Thierry Surply ,  Christophe Bourdeau

    IPC分类号： B64D29/00 ,  B64C21/04

    CPC分类号： B64C21/04 ,  B64D29/02 ,  B64D33/02 ,  B64D2033/0226 ,  Y02T50/166

    摘要： An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are arranged in an alternating fashion from one surface to the next, allowing air to pass on both sides of the aerodynamic surface.

    摘要翻译： 飞行器前缘由提供空气动力学流动的空气动力学表面延伸，并且其中设置空气排放物防止空气动力学流分离。 空气排放物布置成至少两行，基本上平行于前缘并且以偏移方式布置成至少两个连续的行。 在形成空气动力学表面的两个壁之间插入至少一个块。 一方面，该块包括延伸空气动力学表面的外表面，接触形成空气动力学表面的第一壁的第一倾斜表面和接触形成空气动力学表面的第二壁的第二倾斜表面，另一方面 手，突出和/或中空形状，其在倾斜表面处制成并且以从一个表面到下一个表面交替的方式布置，允许空气在空气动力学表面的两侧通过。

    AIRCRAFT NACELLE COMPRISING A REINFORCED OUTER WALL
    8.
    发明申请
    AIRCRAFT NACELLE COMPRISING A REINFORCED OUTER WALL 有权
    包括增强外墙的飞机零件

    公开(公告)号：US20120060938A1

    公开(公告)日：2012-03-15

    申请号：US13258588

    申请日：2010-03-26

    申请人： Frédéric Chelin ,  Thierry Surply

    发明人： Frédéric Chelin ,  Thierry Surply

    IPC分类号： F02K99/00

    CPC分类号： B64D33/02 ,  B64C7/02 ,  F02C7/04 ,  F05D2240/14 ,  F05D2260/602 ,  Y02T50/671 ,  Y10T137/0536

    摘要： An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).

    摘要翻译： 飞机机舱包括限定内部管道（42）的壁，所述内部管道（42）将空气流通向发电厂，在前部的唇缘（44）处并且在外部限定空腔（54）的外壁（46） ，其中所述外壁在其内表面包括布置在横向平面中的至少一个加强件（58），其特征在于，所述至少一个加强件（58）包括允许液体流动的至少一个排水开口 通过所述加强件（58）沿着位于远离所述唇缘的排出口（56）的方向，以限制空气被吸入所述空腔（54）内的风险。

    Turbojet nacelle and method for controlling separation in a turbojet nacelle
    9.
    发明授权
    Turbojet nacelle and method for controlling separation in a turbojet nacelle 失效
    涡轮喷气发动机舱和控制涡轮喷气发动机舱分离的方法

    公开(公告)号：US08640986B2

    公开(公告)日：2014-02-04

    申请号：US12326604

    申请日：2008-12-02

    申请人： Thierry Surply ,  Christophe Bourdeau

    发明人： Thierry Surply ,  Christophe Bourdeau

    IPC分类号： B64D33/02 ,  B64C21/04

    CPC分类号： B64D33/02 ,  B64D2033/0226

    摘要： An aircraft turbojet nacelle comprising blowing means intended to inject a tangential airflow (Ft) into the internal volume (V) of the nacelle, said blowing means being provided in a wall of the air intake of the nacelle in the supersonic area of said air intake. The invention also concerns a method for controlling separation in an aircraft nacelle, wherein a tangential airflow is injected (Ft) into the internal volume (V) of the nacelle in the locally supersonic area of the air intake so as to pull the main airflow (F) into the extension of the inner wall of the nacelle.

    摘要翻译： 一种飞机涡轮喷气发动机舱，包括用于将切向气流（Ft）注入到机舱的内部容积（V）中的吹入装置，所述吹风装置设置在所述进气口的超音速区域中的机舱的进气口的壁中 。 本发明还涉及一种用于控制飞机机舱中的分离的方法，其中将切向气流（Ft）注入到进气口的局部超音速区域中的机舱的内部体积（V）中，以便拉动主气流 F）进入机舱内壁的延伸部分。

    Jet engine nacelle for an aircraft and aircraft comprising such a nacelle
    10.
    发明授权
    Jet engine nacelle for an aircraft and aircraft comprising such a nacelle 有权
    用于包括这种机舱的飞机和飞机的喷气发动机机舱

    公开(公告)号：US07818958B2

    公开(公告)日：2010-10-26

    申请号：US12443343

    申请日：2007-09-28

    申请人： Guillaume Bulin ,  Patrick Oberle ,  Thierry Surply

    发明人： Guillaume Bulin ,  Patrick Oberle ,  Thierry Surply

    IPC分类号： F02K3/04

    CPC分类号： F02K3/06 ,  F02K1/09 ,  F02K1/28 ,  Y02T50/671

    摘要： A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening.

    摘要翻译： 用于飞机高旁路喷气发动机的机舱，其中安装有具有纵向轴线的喷气发动机，所述机舱包括壁同心并且至少部分地围绕喷气发动机并且与后者一起限定用于流体内部流动的环形管道， 包括在所述机舱壁的下游端处具有流出口的通道部分。 机舱包括位移机构，根据要求移动机舱壁的一部分，以改变流出口的通道部分，流体出口的主要部分通过该通道部分排出，在机舱壁中形成至少一个开口的位移，小部分 的泄漏流，自然逃脱。 机舱还包括流体装置，其使用流体来迫使泄漏流沿着相对于至少一个开口下游的机舱壁的部分的外表面流动。