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1. 发明授权

US07818958B2 Jet engine nacelle for an aircraft and aircraft comprising such a nacelle 有权
标题翻译：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。

2. 发明申请

US20090199536A1 PROCESS FOR REVERSING THE THRUST PRODUCED BY A PROPULSION UNIT OF AN AIRCRAFT, DEVICE FOR ITS IMPLEMENTATION, NACELLE EQUIPPED WITH SAID DEVICE 审中-公开
标题翻译：用于反转由飞机的推进单元产生的扭矩的过程，用于其实施的装置，装有设备的装置
公开(公告)号：US20090199536A1
公开(公告)日：2009-08-13
申请号：US12307483
申请日：2007-06-28
申请人： Guillaume Bulin , Patrick Oberle , Thierry Surply
发明人： Guillaume Bulin , Patrick Oberle , Thierry Surply
IPC分类号： F02K3/02
CPC分类号： F02K3/06 , F02K1/09 , F02K1/28 , F02K1/30 , F02K1/32 , F02K1/34 , F02K1/70 , F02K1/72 , Y02T50/671
摘要： The object of the invention is a process whose purpose is to reduce, cancel or reverse the thrust generated by at least one air flow exiting from a propulsion unit of an aircraft by deflecting at least a portion of the flow that is able to assist the thrust, characterized in that it consists in injecting at the level of the propulsion unit a fluid called a thrust reversal fluid to deflect by an entrainment effect, from the inside of the nacelle toward the outside of the nacelle, at least a portion of the flow that is able to assist the thrust.
摘要翻译：本发明的目的是一种方法，其目的是通过使能够协助推力的至少一部分流动来减少，抵消或扭转由飞行器的推进单元离开的至少一个气流产生的推力其特征在于，其包括在所述推进单元的水平面处喷射称为推力反向流体的流体，以通过夹带效应从所述机舱的内部朝向所述机舱的外部偏转所述流动的至少一部分，能够帮助推力。

3. 发明申请

US20100044503A1 JET ENGINE NACELLE FOR AN AIRCRAFT AND AIRCRAFT COMPRISING SUCH A NACELLE 有权
标题翻译：用于飞机的喷气式发动机和包含这样一个空气的飞机
公开(公告)号：US20100044503A1
公开(公告)日：2010-02-25
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： B64C7/02 , B64D29/00 , F02K3/02
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。

4. 发明申请

US20090277155A1 NACELLE FOR AIRCRAFT JET ENGINE AND AIRCRAFT INCLUDING SUCH NACELLE 有权
标题翻译：飞机喷气机发动机和包括这种起重机的飞机
公开(公告)号：US20090277155A1
公开(公告)日：2009-11-12
申请号：US12521869
申请日：2007-12-27
申请人： Guillaume Bulin , Patrick Oberle , Thierry Surply
发明人： Guillaume Bulin , Patrick Oberle , Thierry Surply
IPC分类号： F02K3/02
CPC分类号： B64C7/02 , F02K1/28 , F02K1/30 , F02K1/72 , F02K3/06 , F05D2260/60 , F05D2270/173 , F05D2270/18 , Y02T50/671
摘要： The invention relates to a nacelle, for an aircraft jet engine (10) having a high bypass ratio, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle (12) including a wall (24) concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct (26) for a fluid internal flow having, at the downstream end of the nacelle wall, a flow outlet passage section, characterised in that the nacelle includes displacement means (40) for controllably displacing a portion (24b) of the nacelle wall in order to modify the section of the flow outlet passage, wherein said displacement generates in the nacelle wall at least one longitudinally extending opening (28), the nacelle including a device (30) for forming a fluid barrier (fi) extending along a portion at least of the longitudinal extent of said at least one opening (28) in order to counteract the natural exhaust through said at least one opening of a portion of the so-called trailing flow.
摘要翻译：本发明涉及一种用于具有高旁路比的飞机喷气发动机（10）的机舱，其中安装有具有纵向轴线（X）的喷气发动机，所述机舱（12）包括壁（24），同心且位于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的环形管道（26），其在机舱壁的下游端处具有流出口通道部分，其特征在于，所述机舱包括位移装置（40）用于可控地移动所述机舱壁的一部分（24b）以改变所述流出口通道的所述部分，其中所述位移在所述机舱壁中产生至少一个纵向延伸的开口（28），所述机舱包括装置（30）用于形成沿着所述至少一个开口（28）的纵向范围的至少一部分延伸的流体屏障（fi），以抵消所述自然排气通过所述尾迹的一部分的所述至少一个开口 g流。

5. 发明授权

US08925295B2 Air discharging device for an aircraft double-flow turbine engine 有权
标题翻译：用于飞机双流涡轮发动机的排气装置
公开(公告)号：US08925295B2
公开(公告)日：2015-01-06
申请号：US13235706
申请日：2011-09-19
申请人： Guillaume Bulin , Thierry Surply
发明人： Guillaume Bulin , Thierry Surply
IPC分类号： F02K3/075 , F02K1/12 , F02K1/70 , B64D29/00 , F02K1/82
CPC分类号： F02K1/70 , B64D29/00 , F02K1/12 , F02K1/827 , Y02T50/671
摘要： An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).
摘要翻译：一种用于飞行器涡轮发动机的排气装置（20），包括至少一个门（24），所述门可在对应的孔口（30）的打开和关闭位置之间移动并且包括两个阀门（26,28），其在它们之间界定用于沿下游方向向外引导二次流（76）的一部分（74）并彼此成一体并围绕枢转轴线（58）铰接的导管（68），使得在所述打开位置，所述内阀（26）的上游端相对于内表面（12）从内侧突出，所述外阀（28）的下游端相对于外表面（14）从外侧突出，并且所述内部阀（26）与固定结构（22）间隔开，使得在所述内部阀（26）的下游，后者和所述固定结构（22）之间存在空气通道。

6. 发明授权

US08596037B2 Nacelle with a displacement device for aircraft jet engine and aircraft including such nacelle 有权
标题翻译：具有用于飞机喷气发动机和包括这种机舱的飞机的位移装置的机舱
公开(公告)号：US08596037B2
公开(公告)日：2013-12-03
申请号：US12521869
申请日：2007-12-27
申请人： Guillaume Bulin , Patrick Oberle , Thierry Surply
发明人： Guillaume Bulin , Patrick Oberle , Thierry Surply
IPC分类号： F02K3/02
CPC分类号： B64C7/02 , F02K1/28 , F02K1/30 , F02K1/72 , F02K3/06 , F05D2260/60 , F05D2270/173 , F05D2270/18 , Y02T50/671
摘要： A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.
摘要翻译：对于具有高旁路比的飞机喷气发动机，其中安装有具有纵向轴线的喷气发动机的机舱。机舱包括同心且至少部分地围绕喷气发动机并且一起限定环形管道的壁。机舱还包括位移装置，其可控地移动机舱壁的一部分，以便改变流出口通道的部分并形成至少一个纵向延伸的开口。用于沿着至少一个纵向延伸的开口形成流体屏障的装置被提供以抵消自然排气。

7. 发明申请

US20120073262A1 AIR DISCHARGING DEVICE FOR AN AIRCRAFT DOUBLE-FLOW TURBINE ENGINE 有权
标题翻译：用于飞机双流涡轮发动机的空气排放装置
公开(公告)号：US20120073262A1
公开(公告)日：2012-03-29
申请号：US13235706
申请日：2011-09-19
申请人： Guillaume BULIN , Thierry Surply
发明人： Guillaume BULIN , Thierry Surply
IPC分类号： F02K3/02
CPC分类号： F02K1/70 , B64D29/00 , F02K1/12 , F02K1/827 , Y02T50/671
摘要： An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).
摘要翻译：一种用于飞行器涡轮发动机的排气装置（20），包括至少一个门（24），所述门可在对应的孔口（30）的打开和关闭位置之间移动并且包括两个阀门（26,28），其在它们之间界定用于沿下游方向向外引导二次流（76）的一部分（74）并彼此成一体并围绕枢转轴线（58）铰接的导管（68），使得在所述打开位置，所述内阀（26）的上游端相对于内表面（12）从内侧突出，所述外阀（28）的下游端相对于外表面（14）从外侧突出，并且所述内部阀（26）与固定结构（22）间隔开，使得在所述内部阀（26）的下游，后者和所述固定结构（22）之间存在空气通道。

8. 发明授权

US09003760B2 Acoustic processing panel, more particularly adapted for an air intake in an aircraft nacelle 有权
标题翻译：声学处理面板，更特别适用于飞机机舱中的进气口
公开(公告)号：US09003760B2
公开(公告)日：2015-04-14
申请号：US13145685
申请日：2010-01-29
申请人： Frédéric Chelin , Thierry Surply , Dominique Haro , Fabrice Gantie , David Lambert
发明人： Frédéric Chelin , Thierry Surply , Dominique Haro , Fabrice Gantie , David Lambert
IPC分类号： B64D15/04 , F02C7/047 , F02C7/045 , B64D33/02 , F02K1/82
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/047 , F02K1/827 , Y10T137/0536
摘要： An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.
摘要翻译：连接到飞机机舱的进气口的声学处理面板包括至少一个声阻构造（30）和反射层（32），它们位于基本垂直于纵向方向的方向上（34）的肺泡细胞间隔开以允许用于霜冻治疗的热空气的通过，其特征在于，其包括用于热空气的管（36），每个管（36）分别由至少一个隔板从隔音层（30）延伸到反射层（32），以使得单元的带（34）在纵向方向上绝缘。

9. 发明申请

US20120060938A1 AIRCRAFT NACELLE COMPRISING A REINFORCED OUTER WALL 有权
标题翻译：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。

10. 发明授权

US08640986B2 Turbojet nacelle and method for controlling separation in a turbojet nacelle 失效
标题翻译：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。

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