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1. 发明申请

US20110219783A1 TURBOJET ENGINE NACELLE WITH TRANSLATABLE UPSTREAM COWL 有权
标题翻译： TURBOJET发动机带可翻转UPSTREAM COWL
公开(公告)号：US20110219783A1
公开(公告)日：2011-09-15
申请号：US13129290
申请日：2009-08-28
申请人： Jean-Philippe Joret , Guy Bernard Vauchel , Denis Guillois , Stephane Beilliard
发明人： Jean-Philippe Joret , Guy Bernard Vauchel , Denis Guillois , Stephane Beilliard
IPC分类号： F02C7/20
CPC分类号： B64D29/08 , B64D2033/0286 , F02C7/04
摘要： Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inner panel of the air intake structure, characterized in that the longitudinal outer panel (40) is associated with guide means of the rails (15)/slide (16) type, at least part of said guide means being positioned as close as possible to an interface with a pylon (2) to which the nacelle is attached.
摘要翻译：涡轮喷气发动机机舱（1）包括能够将涡流引导到涡轮喷气发动机的风扇的进气结构（4），以及旨在围绕所述风扇并且进气结构附接到其上的中心结构（5）以确保空气动力学连续性的方式，中心结构一方面包括旨在围绕风扇的壳体，另一方面包括外部结构，其特征在于，进气结构包括纵向外板（40），其包括进气口（4a），并且其可以延伸到至少包括所述中心部分的外部结构的至少一部分并且超出所述外部结构，所述纵向外部面板在操作位置之间可平移地移动，在所述操作位置中，确保机舱外部的空气动力学连续性，以及将外板（40）远离中心部分的外部结构和进气口（4a）设置的维护位置，远离进气结构的内板，其特征在于，纵向外板（40）与导轨（15）/滑块（16）类型的导向装置相关联，所述导向装置的至少一部分被定位尽可能靠近与机架相连的塔架（2）的接口。

2. 发明授权

US09211956B2 Turbojet engine nacelle with translatable upstream cowl 有权
标题翻译：涡轮喷气发动机舱与可翻转的上游整流罩
公开(公告)号：US09211956B2
公开(公告)日：2015-12-15
申请号：US13129290
申请日：2009-08-28
申请人： Jean-Philippe Joret , Guy Bernard Vauchel , Denis Guillois , Stephane Beilliard
发明人： Jean-Philippe Joret , Guy Bernard Vauchel , Denis Guillois , Stephane Beilliard
IPC分类号： F02C7/20 , F02C7/04 , B64D29/08
CPC分类号： B64D29/08 , B64D2033/0286 , F02C7/04
摘要： Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inner panel of the air intake structure, characterized in that the longitudinal outer panel (40) is associated with guide means of the rails (15)/slide (16) type, at least part of said guide means being positioned as close as possible to an interface with a pylon (2) to which the nacelle is attached.
摘要翻译：涡轮喷气发动机机舱（1）包括能够将涡流引导到涡轮喷气发动机的风扇的进气结构（4），以及旨在围绕所述风扇并且进气结构附接到其上的中心结构（5）以确保空气动力学连续性的方式，中心结构一方面包括旨在围绕风扇的壳体，另一方面包括外部结构，其特征在于，进气结构包括纵向外板（40），其结合有进气口（4a），并且其可以延伸到至少包括所述中心部分的外部结构的至少一部分并且超出所述外部结构，所述纵向外部面板在操作位置之间可平移地移动，在所述操作位置中，确保机舱外部的空气动力学连续性，以及将外板（40）远离中心部分的外部结构和进气口（4a）设置的维护位置，远离进气结构的内板，其特征在于，纵向外板（40）与导轨（15）/滑块（16）类型的导向装置相关联，所述导向装置的至少一部分被定位尽可能靠近与机架相连的塔架（2）的接口。

3. 发明授权

US08739552B2 Structural nacelle 失效
标题翻译：结构机舱
公开(公告)号：US08739552B2
公开(公告)日：2014-06-03
申请号：US12302998
申请日：2007-06-11
申请人： Guy Bernard Vauchel , Anne-Laure Gibouin , Regis Fassier , Jean-Philippe Joret , Jerome Collier , Guillaume Lefort , Pierre-Alain Chouard
发明人： Guy Bernard Vauchel , Anne-Laure Gibouin , Regis Fassier , Jean-Philippe Joret , Jerome Collier , Guillaume Lefort , Pierre-Alain Chouard
IPC分类号： F01D25/30 , B64D27/00
CPC分类号： B64D29/00 , B64D27/18
摘要： The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.
摘要翻译：本发明一方面涉及一种用于双流涡轮反应器（2）的机舱（1），其包括前进气部分（5），中间部分（6），用于围绕所述风机涡轮反应器和后部部分（7），所述后部部分具有旨在用作到所述涡轮反应器的后部的壳体的内部结构（7b），其特征在于，所述内部结构具有适于使所述机舱被紧固的附接装置连接到在所述内部结构的至少一部分上连接到飞机的固定结构（13）的塔架（12），另一方面，连接到具有这种机舱的飞行器。

4. 发明授权

US09249756B2 Assembly for an aircraft turbojet engine comprising a thrust reversal cowl 有权
标题翻译：用于包括推力反转罩的飞行器涡轮喷气发动机的组装
公开(公告)号：US09249756B2
公开(公告)日：2016-02-02
申请号：US13511279
申请日：2010-11-25
申请人： Pierre Caruel , Guy Bernard Vauchel , Jean-Philippe Joret , Andre Baillard
发明人： Pierre Caruel , Guy Bernard Vauchel , Jean-Philippe Joret , Andre Baillard
IPC分类号： F02K1/72 , F02K1/76 , B64D29/06
CPC分类号： F02K1/766 , B64D29/06 , F02K1/72
摘要： The invention relates to an assembly for a turbojet engine which includes a pylon (1) and a nacelle supported by said pylon (1). Said nacelle (3) includes a grid thrust reverser (21) including an integral cowl mounted so as to slide on rails (15), which are arranged on both sides of said pylon (1), between a direct jet position and a thrust reversal position. Said assembly is characterized in that it includes means (23, 31) for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon (1) and the cowl.
摘要翻译：本发明涉及一种用于涡轮喷气发动机的组件，其包括塔架（1）和由所述塔架（1）支撑的机舱。所述机舱（3）包括格栅推力反向器（21），其包括安装成在所述塔架（1）的两侧上的导轨（15）之间在直接喷射位置和推力反向位置。所述组件的特征在于它包括用于阻挡整流罩在轨道（15）上的滑动运动的装置（23,31），所述装置插入在塔架（1）和整流罩之间。

5. 发明申请

US20110214405A1 NACELLE AIR INTAKE STRUCTURE 审中-公开
标题翻译： NACELLE空气采集结构
公开(公告)号：US20110214405A1
公开(公告)日：2011-09-08
申请号：US13129226
申请日：2009-10-23
申请人： Jean-Philippe Joret , Guy Bernard Vauchel
发明人： Jean-Philippe Joret , Guy Bernard Vauchel
IPC分类号： F16P1/00
CPC分类号： B64D29/08 , B64D29/06 , B64D2033/0286
摘要： The invention relates to a nacelle comprising an air intake structure (1) able to channel a flow of air towards a fan of the turbojet engine, said structure (1) comprising at least one inner panel (11) and one outer panel (10), the outer panel (10) being able to be moved by guide means (30) so as to open up the air intake structure (1), characterized in that it further comprises means (40, 60) for protecting the inner panel (11) against fire, said means being able to be moved in whole or in part when the air intake structure (1) is opened.
摘要翻译：本发明涉及一种机舱，其包括能够将空气流引导到涡轮喷气发动机的风扇的进气结构（1），所述结构（1）包括至少一个内板（11）和一个外板（10），所述外板（10）能够通过引导装置（30）移动以便打开所述进气结构（1），其特征在于，还包括用于保护所述内板（11）的装置（40,60）），所述装置能够在进气结构（1）打开时全部或部分移动。

6. 发明申请

US20090255271A1 STRUCTURAL NACELLE 失效
标题翻译：结构化NACELLE
公开(公告)号：US20090255271A1
公开(公告)日：2009-10-15
申请号：US12302998
申请日：2007-06-11
申请人： Guy Bernard Vauchel , Anne-Laure Gibouin , Regis Fassier , Jean-Philippe Joret , Jerome Collier , Guillaume Lefort , Pierre-Alain Chouard
发明人： Guy Bernard Vauchel , Anne-Laure Gibouin , Regis Fassier , Jean-Philippe Joret , Jerome Collier , Guillaume Lefort , Pierre-Alain Chouard
IPC分类号： F02C7/20
CPC分类号： B64D29/00 , B64D27/18
摘要： The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterised in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle.
摘要翻译：本发明一方面涉及一种用于双流涡轮反应器（2）的机舱（1），其包括前进气部分（5），中间部分（6），用于围绕所述风机涡轮反应器和后部部分（7），所述后部部分具有旨在用作到所述涡轮反应器的后部的壳体的内部结构（7b），其特征在于，所述内部结构具有适于使所述机舱被紧固的附接装置连接到在所述内部结构的至少一部分上连接到飞机的固定结构（13）的塔架（12），另一方面，连接到具有这种机舱的飞行器。

7. 发明申请

US20120247571A1 JET ENGINE NACELLE REAR ASSEMBLY 审中-公开
标题翻译：喷气机发动机零件组件
公开(公告)号：US20120247571A1
公开(公告)日：2012-10-04
申请号：US13514554
申请日：2010-11-26
申请人： Guy Bernard Vauchel , Pierre Caruel , Jean-Philippe Joret
发明人： Guy Bernard Vauchel , Pierre Caruel , Jean-Philippe Joret
IPC分类号： F02B77/00
CPC分类号： B64D29/06 , B64D29/08 , F01D25/243 , F02K1/80 , Y10T137/0536
摘要： The present invention relates to a nacelle rear assembly (1) including a pod-shaped internal structure (11), said internal structure comprising at least one downstream portion (15) and one upstream portion (13) that are each movably mounted between an operative position, in which said portions are connected, and at least one maintenance position, in which said portions are separate from each other, the downstream portion being movably mounted by means of sliding while the upstream portion is movable by opening at least one door. The downstream portion and upstream portion are provided with a connection means that is capable of engaging therebetween. Said assembly is characterized in that at least one of the downstream and upstream portions is provided with a hinging means (131, 151) having a range of movement in at least one direction so as to enable stress-free control and operation of the portion in question.
摘要翻译：本发明涉及一种包括荚状内部结构（11）的机舱后部组件（1），所述内部结构包括至少一个下游部分（15）和一个上游部分（13），每个下游部分（15）和一个上游部分（13）位置，其中所述部分被连接，以及至少一个维护位置，其中所述部分彼此分离，所述下游部分通过滑动可移动地安装，同时上游部分通过打开至少一个门而可移动。下游部分和上游部分设置有能够在其间接合的连接装置。所述组件的特征在于，所述下游部分和上游部分中的至少一个设置有铰链装置（131,151），所述铰接装置具有在至少一个方向上的运动范围，以便能够对所述部分进行无应力控制和操作题。

8. 发明申请

US20120228403A1 ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE COMPRISING A THRUST REVERSAL COWL 有权
标题翻译：用于包含反转轮的飞机涡轮发动机的组装
公开(公告)号：US20120228403A1
公开(公告)日：2012-09-13
申请号：US13511279
申请日：2010-11-25
申请人： Pierre Caruel , Guy Bernard Vauchel , Jean-Philippe Joret , Andre Baillard
发明人： Pierre Caruel , Guy Bernard Vauchel , Jean-Philippe Joret , Andre Baillard
IPC分类号： B64D33/04
CPC分类号： F02K1/766 , B64D29/06 , F02K1/72
摘要： The invention relates to an assembly for a turbojet engine which includes a pylon (1) and a nacelle supported by said pylon (1). Said nacelle (3) includes a grid thrust reverser (21) including an integral cowl mounted so as to slide on rails (15), which are arranged on both sides of said pylon (1), between a direct jet position and a thrust reversal position. Said assembly is characterised in that it includes means (23, 31) for blocking the sliding movement of the cowl on the rails (15), said means being inserted between the pylon (1) and the cowl.
摘要翻译：本发明涉及一种用于涡轮喷气发动机的组件，其包括塔架（1）和由所述塔架（1）支撑的机舱。所述机舱（3）包括格栅推力反向器（21），其包括安装成在所述塔架（1）的两侧上的导轨（15）之间在直接喷射位置和推力反向位置。所述组件的特征在于它包括用于阻挡整流罩在轨道（15）上的滑动运动的装置（23,31），所述装置插入在塔架（1）和整流罩之间。

9. 发明申请

US20100218480A1 ACTUATOR FOR AN AIRCRAFT NACELLE MOBILE STRUCTURE, AND NACELLE COMPRISING AT LEAST ONE SUCH ACTUATOR 失效
标题翻译：用于航空器移动结构的执行器，以及至少包括一个这样的致动器的起动器
公开(公告)号：US20100218480A1
公开(公告)日：2010-09-02
申请号：US12682139
申请日：2008-09-12
申请人： Guy Vauchel , Jean-Philippe Joret , Pierre Baudu , Christophe Guenadou
发明人： Guy Vauchel , Jean-Philippe Joret , Pierre Baudu , Christophe Guenadou
IPC分类号： F02K1/76 , F02K1/54
CPC分类号： F02K1/763 , B64D29/06 , F16H25/20 , F16H2025/2037
摘要： This actuator for an aircraft engine nacelle mobile structure (9) comprises a motor (1) intended to be mounted on a fixed part of the said nacelle, an endless screw (21) able to be turned by this motor (1), a slideway (5) intended to be connected to the said mobile structure (9) and comprising a nut (29) in mesh with the said endless screw, and a first ball end (15) allowing an angular offset between the axis of the said endless screw (21) and the said slideway (5). This actuator is notable in that it comprises a sleeve (19) able to accommodate the said screw (21) and extending with clearance inside the said slideway (5), the said nut (29) being mounted on that end of the said sleeve (19) that is closest to the said motor (1), and the said first ball end being interposed between the other end of the said sleeve (19) and the said slideway (5).
摘要翻译：用于飞机发动机机舱移动结构（9）的致动器包括：将要安装在所述机舱的固定部分上的电动机（1），能够被该马达（1）转动的环形螺钉（21），滑道（5），其旨在连接到所述移动结构（9）并且包括与所述环形螺钉啮合的螺母（29）和允许所述环形螺钉的轴线之间的角度偏移的第一球形端（15）（21）和所述滑道（5）。该致动器的特征在于它包括能够容纳所述螺钉（21）并且在所述滑道（5）内部的间隙延伸的套筒（19），所述螺母（29）安装在所述套筒的所述端部 19），并且所述第一球端插入在所述套筒（19）的另一端和所述滑道（5）之间。

10. 发明申请

US20100327110A1 GUIDING SYSTEM FOR AIRCRAFT NACELLE MAINTENANCE 有权
标题翻译：飞机维修指导系统
公开(公告)号：US20100327110A1
公开(公告)日：2010-12-30
申请号：US12864925
申请日：2009-01-21
申请人： Pierre Caruel , Jean-Philippe Joret , Peter Segat
发明人： Pierre Caruel , Jean-Philippe Joret , Peter Segat
IPC分类号： B64D27/12 , F01D25/24 , F02K9/00
CPC分类号： B64D29/08
摘要： The invention relates to a nacelle (100) for the turbojet of an aircraft that comprises a downstream structure including: an outer structure (106), a concentric inner structure (109) surrounding a downstream portion (111) of the turbojet and including an upstream section having a relatively small diameter (113) and a downstream section having a relatively large diameter (114), wherein said inner structure (109) defines together with the outer structure (106) an annular flow channel (108); and a guiding system (140) for connecting the inner structure (109) and the downstream portion (111) of the turbojet engine or a portion of a suspension mast; characterised in that the guiding system (140) includes a means for combining a translation and rotation movement of at least a portion of said inner structure (109) between a working position, in which the inner structure (109) is used as a cowling for the turbojet downstream portion (111), and a maintenance position in which the inner structure (109) exposes said turbojet downstream portion (111), thus enabling the movement of said portion if the inner structure (109) along the profile of the upstream section having a relatively small diameter (113), and then of the downstream section having a relatively large diameter (114).
摘要翻译：本发明涉及一种用于飞行器涡轮喷气发动机的机舱（100），其包括下游结构，其包括：外部结构（106），围绕涡轮喷气发动机的下游部分（111）的同心内部结构（109），并且包括上游具有相对较小直径（113）的截面和具有相对较大直径（114）的下游部分，其中所述内部结构（109）与所述外部结构（106）一起限定环形流动通道（108）; 以及用于连接涡轮喷气发动机的内部结构（109）和下游部分（111）或悬架杆的一部分的引导系统（140）其特征在于，所述引导系统（140）包括用于将所述内部结构（109）的至少一部分的平移和旋转运动组合在工作位置之间的装置，其中所述内部结构（109）用作整流罩所述涡轮喷气下游部分（111）以及所述内部结构（109）暴露所述涡轮喷气下游部分（111）的维护位置，从而如果所述内部结构（109）沿着所述上游部分具有相对小的直径（113），然后具有相对较大直径（114）的下游部分。

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