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1. 发明授权

US09284060B2 Aircraft nacelle including a rear frame inclined to the rear 有权
标题翻译：飞机机舱包括一个向后倾斜的后框架
公开(公告)号：US09284060B2
公开(公告)日：2016-03-15
申请号：US13270536
申请日：2011-10-11
申请人： Alain Porte , Jacques Lalane , Frederic Chelin
发明人： Alain Porte , Jacques Lalane , Frederic Chelin
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0206 , B64D2033/0286 , Y10T137/0536
摘要： An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.
摘要翻译：飞机机舱包括其表面与空气动力流接触的唇缘，其通过内壁在内部壁延伸，所述内壁限定通过外壁在发电厂和机舱外部排空的层，第一前框架连接内外围绕边缘限定一个环形管，并且后框架在内管和发电厂管之间的接合区连接内壁和外壁，对于机舱的给定横截面沿着包含纵向轴线的平面机舱，后框架和内壁之间的交点处的点A和后框架与外壁之间的交叉点处的点B，其中B相对于A更靠近机舱的后部超过后框架周边的50％。

2. 发明授权

US09719422B2 Process for the production of an acoustic treatment panel that integrates channels juxtaposed with an alveolar structure 有权
公开(公告)号：US09719422B2
公开(公告)日：2017-08-01
申请号：US13527100
申请日：2012-06-19
申请人： Alain Porte , Frederic Chelin
发明人： Alain Porte , Frederic Chelin
IPC分类号： B21D47/00 , F02C7/045 , B64D33/02
CPC分类号： F02C7/045 , B21D47/00 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F05D2250/283 , Y02T50/672
摘要： A process for the production of an acoustic treatment panel that includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), as well as at least one channel that is bordered at least in part by a wall (32) that is secant with at least one wall of a cell of the alveolar structure (26), includes elevating the temperature of the wall (32) and the ends of the cells of the alveolar structure (26) and injecting a pressurized gas into the channel (30) so as to expand the wall (32) of the channel so as to flatten it against the ends of the cells of the alveolar structure (26) in such a way as to produce a weld by continuous diffusion between the ends of the walls of the cells of the alveolar structure (26) and the wall (32) of the channel (30).

3. 发明授权

US08991054B2 Process for the production of a panel for the acoustic treatment incorporating the frost treatment function with hot air 有权
标题翻译：用于生产用于具有热空气的霜处理功能的声学处理面板的方法
公开(公告)号：US08991054B2
公开(公告)日：2015-03-31
申请号：US13527192
申请日：2012-06-19
申请人： Alain Porte , Frederic Chelin , Gregory Albet
发明人： Alain Porte , Frederic Chelin , Gregory Albet
IPC分类号： B64D15/04 , B64D33/02 , F02C7/045 , F02C7/047
CPC分类号： B64D15/04 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/047 , Y02T50/672 , Y10T29/49622 , Y10T29/49826 , Y10T29/49908 , Y10T29/49995
摘要： A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), and channels (30) placed between the alveolar structure and the acoustically resistive layer, each channel being bordered by a wall (32), the process including deforming a layer so as to produce furrows at one of its surfaces, flattening and making integral the deformed layer (34) with the acoustically resistive layer so as to border the channels, and removing material in such a way as to eliminate at least a portion of the thickness of the deformed layer (34) in which the furrows are formed between the channels, prior to the assembly of the alveolar structure.
摘要翻译：声学处理板的制造方法，其可以在飞行器的表面，特别是在诸如飞机机舱的进气口的前缘处连接，由此所述面板包括声阻层（24），在至少一个肺泡结构（26）和反射层（28）以及置于肺泡结构和声阻层之间的通道（30），每个通道由壁（32）界定，该过程包括使层变形为了在其一个表面上产生沟槽，使其变形层（34）平坦化并与声阻层一体化，以便与通道相接触，并且以这样的方式去除材料，以便消除至少一部分厚度的在组装气泡结构之前，在沟槽之间形成沟槽的变形层（34）。

4. 发明授权

US09003810B2 Aircraft cover including means for limiting the scoop phenomena of pneumatic type 有权
标题翻译：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。

5. 发明授权

US08851416B2 Aircraft nacelle including at least one radial partition between two conducts 有权
标题翻译：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。

6. 发明申请

US20090290978A1 TURBINE ENGINE FOR AIRCRAFT 有权
标题翻译：用于飞机的涡轮发动机
公开(公告)号：US20090290978A1
公开(公告)日：2009-11-26
申请号：US12307874
申请日：2007-07-04
申请人： Alain Porte , Frederic Chelin , David Lambert
发明人： Alain Porte , Frederic Chelin , David Lambert
IPC分类号： F01D25/24
CPC分类号： F02C7/04 , F05B2260/301 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F16B5/01 , F16B5/02 , Y02T50/672
摘要： According to the invention, the internal wall (5.1) of the air intake (2) and the housing (12.1) for the fan (3) are pieces of composite fibre/resin material, overlap-jointed at the ends thereof (5.1R) and (12.1A).
摘要翻译：根据本发明，进气口（2）的内壁（5.1）和风扇（3）的壳体（12.1）是复合纤维/树脂材料片，其端部重叠连接（5.1R）和（12.1A）。

7. 发明授权

US09261021B2 Turbine engine for aircraft 有权
标题翻译：用于飞机的涡轮发动机
公开(公告)号：US09261021B2
公开(公告)日：2016-02-16
申请号：US12307886
申请日：2007-07-04
申请人： Alain Porte , Fabrice Gantie , Frederic Chelin , Patrick Oberle
发明人： Alain Porte , Fabrice Gantie , Frederic Chelin , Patrick Oberle
IPC分类号： F02B27/00 , F02C7/04 , F02K3/06
CPC分类号： F02C7/04 , F02K3/06 , F05D2240/14 , F05D2300/603 , Y02T50/672 , Y10T137/0536
摘要： An internal wall of an air intake and a housing of a fan form a single tubular piece made from a fiber/resin composite material. A rear end has the single tubular component connected by a flange and bolts to an external cowl of the fan duct, such that the rear end of the tubular component is uniform and the flange is attached and fixed to the rear end.
摘要翻译：空气入口的内壁和风扇的壳体形成由纤维/树脂复合材料制成的单个管状件。后端具有通过法兰和螺栓连接到风扇管道的外部整流罩的单个管状部件，使得管状部件的后端是均匀的并且凸缘被附接并固定到后端。

8. 发明授权

US08794572B2 Air intake of an aircraft nacelle that incorporates a reinforced lip with a defrost system by joule-effect 有权
标题翻译：飞机机舱的空气进口，通过焦耳效应结合加霜唇与除霜系统
公开(公告)号：US08794572B2
公开(公告)日：2014-08-05
申请号：US13523282
申请日：2012-06-14
申请人： Alain Porte , Frederic Chelin
发明人： Alain Porte , Frederic Chelin
IPC分类号： B64D15/12
CPC分类号： B64D33/02 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286
摘要： An air intake of an aircraft nacelle includes:on the one hand, a lip (42) that is defined by a wall (52) whose surface that is in contact with the aerodynamic flows is extended on the inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant and on the outside of the nacelle by an outside wall (46), and, on the other hand, a surface-type Joule-effect defrosting system (58); at least a first alveolar structure (60.1) that is made of a material that conducts the heat and that is flattened against the inside surface of the wall (52) and inserted between the wall (52) and the defrosting system (58), and at least one second alveolar structure (60.2) that is made of composite material that is adjacent to the first structure (60.1).
摘要翻译：飞机机舱的进气口包括：一方面是由壁（52）限定的唇缘（42），其表面与空气动力学流动接触，其通过内壁延伸在机舱内部（44），其与通过外壁（46）在发电厂和机舱外部排空的管道相接触，另一方面是表面型焦耳效应除霜系统（58）; 至少第一肺泡结构（60.1），其由传导热量的材料制成并且被平坦化抵靠壁（52）的内表面并插入在壁（52）和除霜系统（58）之间，以及至少一个第二肺泡结构（60.2），其由与所述第一结构（60.1）相邻的复合材料制成。

9. 发明授权

US08142144B2 Turbine engine for aircraft 有权
标题翻译：用于飞机的涡轮发动机
公开(公告)号：US08142144B2
公开(公告)日：2012-03-27
申请号：US12307874
申请日：2007-07-04
申请人： Alain Porte , Frederic Chelin , David Lambert
发明人： Alain Porte , Frederic Chelin , David Lambert
IPC分类号： F04D29/40
CPC分类号： F02C7/04 , F05B2260/301 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F16B5/01 , F16B5/02 , Y02T50/672
摘要： Disclosed is an aircraft turbine engine. The turbine engine includes an air intake having a tubular internal wall and a fan enclosed by a tubular fan casing, and the rear end of the said air intake internal wall and the front end of the fan casing are joined together by at least one fastener. The air intake internal wall, the fan casing, or both, are comprised of a resin/fiber composite. The rear end of the air intake internal wall and the front end of the fan casing are uniform, and have no projections that join the internal wall and casing together.
摘要翻译：公开了一种飞机涡轮发动机。涡轮发动机包括具有管状内壁的空气入口和由管状风扇壳体包围的风扇，并且所述进气内壁的后端和风扇壳体的前端通过至少一个紧固件连接在一起。进气内壁，风扇外壳或两者均由树脂/纤维复合材料构成。进气内壁的后端和风扇外壳的前端是均匀的，没有将内壁和外壳连接在一起的突起。

10. 发明申请

US20090255589A1 TURBINE ENGINE FOR AIRCRAFT 有权
标题翻译：用于飞机的涡轮发动机
公开(公告)号：US20090255589A1
公开(公告)日：2009-10-15
申请号：US12307886
申请日：2007-07-04
申请人： Alain Porte , Fabrice Gantie , Frederic Chelin , Patrick Oberle
发明人： Alain Porte , Fabrice Gantie , Frederic Chelin , Patrick Oberle
IPC分类号： F02C7/04
CPC分类号： F02C7/04 , F02K3/06 , F05D2240/14 , F05D2300/603 , Y02T50/672 , Y10T137/0536
摘要： According to the invention, the internal wall of the air intake (2) and the housing of the fan (3) form a single tubular piece (30) made from a fibre/resin composite material.
摘要翻译：根据本发明，进气口（2）的内壁和风扇（3）的壳体形成由纤维/树脂复合材料制成的单个管状件（30）。

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