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11. 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）。

12. 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。

13. 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。

14. 发明申请

US20100327120A1 AIR OUTLET SYSTEM FOR AIRCRAFT LEADING EDGE 有权
标题翻译：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。

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