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1. 发明授权

US08943793B2 Rear section of aircraft nacelle and nacelle equipped with such rear section 有权
标题翻译：飞机机舱和机舱的后部配备有这样的后部
公开(公告)号：US08943793B2
公开(公告)日：2015-02-03
申请号：US12673288
申请日：2008-06-16
申请人： Eric Lecossais , Thierry Ledocte , Pascal Gerard Rouyer , Felix Carimali
发明人： Eric Lecossais , Thierry Ledocte , Pascal Gerard Rouyer , Felix Carimali
IPC分类号： F02K3/02 , B64D29/00
CPC分类号： B64D29/00
摘要： The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterized in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.
摘要翻译：本发明涉及飞机机舱的后部（11），其包括两个半部（13a，13b），其限定：用于容纳涡轮喷气发动机（7）的中央部分（C），冷空气环形通道（31）设置在所述中心部分（C）周围，以及设置在所述中心部分（C）下方的至少一个六小时空腔（15）。后部分的特征在于它包括用于在所述环形通道（31）和所述六小时空腔（15）之间流体连通的至少一个管道（29a，29b），用于保持六小时空腔内的温度（15 ）在相对较低的范围内。

2. 发明申请

US20120000179A1 REAR SECTION OF AIRCRAFT NACELLE AND NACELLE EQUIPPED WITH SUCH REAR SECTION 有权
标题翻译：具有这种后部装备的空中客车和后舱的后部分
公开(公告)号：US20120000179A1
公开(公告)日：2012-01-05
申请号：US12673288
申请日：2008-06-16
申请人： Eric Lecossais , Thierry Ledocte , Pascal Gerard Rouyer , Felix Carimali
发明人： Eric Lecossais , Thierry Ledocte , Pascal Gerard Rouyer , Felix Carimali
IPC分类号： F02K1/52
CPC分类号： B64D29/00
摘要： The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterised in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.
摘要翻译：本发明涉及飞机机舱的后部（11），其包括两个半部（13a，13b），其限定：用于容纳涡轮喷气发动机（7）的中央部分（C），冷空气环形通道（31）设置在所述中心部分（C）周围，以及设置在所述中心部分（C）下方的至少一个六小时空腔（15）。后部分的特征在于它包括用于在所述环形通道（31）和所述六小时空腔（15）之间流体连通的至少一个管道（29a，29b），用于保持六小时空腔内的温度（15 ）在相对较低的范围内。

3. 发明授权

US6032901A Linkage system for an aircraft turbojet engine 失效
标题翻译：飞机涡轮喷气发动机联动系统
公开(公告)号：US6032901A
公开(公告)日：2000-03-07
申请号：US969360
申请日：1997-11-28
申请人： Felix Carimali , Jean-Paul Rene Andre Hogie , Xavier Raymond Yves Lore , Pascal Gerard Rouyer
发明人： Felix Carimali , Jean-Paul Rene Andre Hogie , Xavier Raymond Yves Lore , Pascal Gerard Rouyer
IPC分类号： B64D29/06 , B64D33/00 , F01D25/24 , F02K1/60 , F02K1/80 , B64C1/14
CPC分类号： B64D29/06 , F01D25/24 , F02K1/80 , Y02T50/671 , Y10T292/0837
摘要： A linkage system is disclosed for releasably latching a thrust reverser to an engine casing having a longitudinal axis, the linkage system having a seat on the thrust reverser and a movable latching member on the engine casing movable between an open position in which the latching member is displaced away from the seat, and a closed position in which the latching member is located adjacent to the seat so as to prevent displacement of the thrust reverser away from the engine casing.
摘要翻译：公开了一种联动系统，用于可释放地将推力反向器锁定到具有纵向轴线的发动机壳体上，该联动系统在推力反向器上具有座椅，并且在发动机壳体上的可移动的闩锁构件可在打开位置之间移动，其中闩锁构件离开座椅的位置，以及闭合位置，其中闩锁构件邻近座椅定位，以防止推力反向器远离发动机壳体的位移。

4. 发明授权

US5297387A Deflector edge for a thrust reverser 失效
公开(公告)号：US5297387A
公开(公告)日：1994-03-29
申请号：US931355
申请日：1992-08-18
申请人： Felix Carimali , Michel J. L. Legras
发明人： Felix Carimali , Michel J. L. Legras
IPC分类号： F02K1/56 , F02K1/60 , F02K1/70 , F02K3/02
CPC分类号： F02K1/70 , F02K1/563 , F02K1/60 , F05D2250/71
摘要： A thrust reverser for a turbofan-type turbojet engine assembly is disclosed having a deflector defining an upstream edge of a reverse thrust opening formed in the turbofan housing so as to control the direction and shape of the gases passing through the reverse thrust opening. The deflector has a deflector edge portion defining a deflector edge wherein the curvature of the deflector edge portion, as measured in a longitudinal radial plane passing radially through a longitudinal axis of the engine, varies in a direction from one side of the reverse thrust opening to the opposite side of the opening. The curvature of the deflector edge portion is defined as being positive when the center of curvature of the deflector edge portion lies radially outwardly of the deflector and is defined as being negative when the center of curvature of the deflector edge portion lies radially inwardly of the deflector. The deflector edge portion may have a positive curvature adjacent to one side of the reverse thrust opening and a negative curvature adjacent to an opposite side of the reverse thrust opening such that the deflector edge defines a continuous smooth curve from one side of the reverse thrust opening to the other side. The direction and the shape of the gases passing through the reverse thrust opening is controlled by varying the curvature of the deflector edge portion across the reverse thrust opening. The portion of the deflector edge having a positive curve of the smallest radius forms a maximum flow area, while the deflector edge portion having a negative curvature of the smallest radius forms a minimum flow area. Thus, by tailoring the curvature of the deflector edge portion to meet the requirements of a particular engine/aircraft application, the direction and shape of the gases passing through the reverse thrust opening can be controlled so as to minimize contact with the adjacent aircraft structure and to prevent reingestion of the thrust reverse gases into the turbofan engine.

5. 发明授权

US5284015A Turbojet engine thrust reverser with directional control 失效
标题翻译：涡轮喷气发动机推力反向器带方向控制
公开(公告)号：US5284015A
公开(公告)日：1994-02-08
申请号：US942218
申请日：1992-09-09
申请人： Felix Carimali , Michel J. L. Legras
发明人： Felix Carimali , Michel J. L. Legras
IPC分类号： F02K1/56 , F02K1/60 , F02K1/70 , F02K3/02
CPC分类号： F02K1/70 , F02K1/563 , F02K1/60
摘要： A thrust reverser for a turbojet engine is disclosed having a movable component, such as a thrust reverser door, operatively associated with an engine housing, and vanes formed on the upstream edge portion of the movable component and extending inwardly from an interior surface. The vanes, which extend in a direction generally parallel to a longitudinal axis of the engine, are located in an array which extends across the upstream edge portion of the movable component from one side to the other. The vanes each may be generally triangular in configuration and have one side attached to the inner surface of the movable component and another side attached to a gas flow deflector extending laterally across the front edge of the movable component.
摘要翻译：公开了一种用于涡轮喷气发动机的推力反向器，其具有与发动机壳体可操作地相关联的可移动部件，例如推力反向器门，以及形成在可移动部件的上游边缘部分上并从内表面向内延伸的叶片。沿大致平行于发动机的纵向轴线的方向延伸的叶片位于从可动部件的上游边缘部分的一侧延伸到另一侧的阵列中。叶片各自可以是大致三角形的结构，并且一侧连接到可移动部件的内表面，另一侧附接到横向延伸穿过可移动部件的前边缘的气体导流板。

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