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1. 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。

2. 发明授权

US08523516B2 Bypass turbojet engine nacelle 失效
标题翻译：旁路涡轮喷气发动机舱
公开(公告)号：US08523516B2
公开(公告)日：2013-09-03
申请号：US12445421
申请日：2007-10-05
申请人： Guy Bernard Vauchel , Jerome Collier , Patrice Dhainault , Francois Conte , Nicolas Hillereau , Pierre-Alain Chouard , Guillaume Lefort
发明人： Guy Bernard Vauchel , Jerome Collier , Patrice Dhainault , Francois Conte , Nicolas Hillereau , Pierre-Alain Chouard , Guillaume Lefort
IPC分类号： F03B11/08 , F03B1/00 , F01D5/00 , F01D25/28 , F04D29/44
CPC分类号： B64D27/18 , B64D27/26 , B64D29/08 , B64D33/04 , B64D2027/264 , B64D2027/266 , F02C7/20 , F02K1/72 , F02K3/06 , F05D2300/603 , Y02T50/44 , Y02T50/672
摘要： The nacelle (1) comprises an air intake (5) upstream of the turbojet engine (2), a middle section (6) an internal casing (6a) of which is intended to surround a fan (3) of the turbojet engine (2), and a downstream section (7) comprising an external structure (7a)which is rigidly connected to a downstream part of the casing (6a) of the fan (3) so as to support the turbojet engine (2) and has means of attachment to a strut (12) intended to be connected to a fixed structure (13) of an aeroplane.
摘要翻译：机舱（1）包括在涡轮喷气发动机（2）上游的进气口（5），中间部分（6），其内部壳体（6a）旨在围绕涡轮喷气发动机（2）的风扇（3））和包括外部结构（7a）的下游部分（7），其刚性地连接到风扇（3）的壳体（6a）的下游部分，以支撑涡轮喷气发动机（2），并具有连接到旨在连接到飞机的固定结构（13）的支柱（12）。

3. 发明申请

US20090134271A1 TURBOJET SUSPENDED FROM AN AIRCRAFT MAST 有权
标题翻译：涡轮机悬挂在飞机上
公开(公告)号：US20090134271A1
公开(公告)日：2009-05-28
申请号：US12275815
申请日：2008-11-21
申请人： Andre Bruno Denis Baillard , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Francois Raymond Conte , Guillaume Lefort
发明人： Andre Bruno Denis Baillard , Pierre-Alain Jean-Marie Philippe Hugues Chouard , Francois Raymond Conte , Guillaume Lefort
IPC分类号： B64D27/00
CPC分类号： B64D27/26
摘要： The present invention relates to a turbojet suspended from an aircraft mast, the turbojet comprising a front fan, an intermediate casing downstream of the fan with an outer shroud and a hub connected together by radial arms and an exhaust casing with an outer shroud, the two casings being aligned on one and the same axis XX, the mast comprising a structural strut assembly of elongated shape. In said turbojet said strut assembly is attached upstream rigidly to said outer shroud of the intermediate casing by a front attachment comprising a means for transmitting the axial and lateral forces and downstream by a rear attachment to said exhaust casing.
摘要翻译：本发明涉及从飞机桅杆悬挂的涡轮喷气发动机，涡轮喷气发动机包括前风扇，风扇下游具有外护罩的中间壳体和通过径向臂连接在一起的轮毂和具有外护罩的排气外壳，壳体在同一轴线XX上对准，桅杆包括细长形状的结构支柱组件。在所述涡轮喷气发动机中，所述支柱组件通过前连接件刚性地附接到所述中间壳体的所述外护罩上，所述前附件包括用于传递所述轴向力和侧向力的装置，并且通过后附件向下排排放到所述排气外壳。

4. 发明授权

US08104708B2 Suspension for mounting a turbojet engine on an aircraft 有权
标题翻译：悬挂在飞机上安装涡轮喷气发动机
公开(公告)号：US08104708B2
公开(公告)日：2012-01-31
申请号：US12329136
申请日：2008-12-05
申请人： Pierre-Alain Jean-Marie Philippe Hugues Chouard , Guillaume Lefort
发明人： Pierre-Alain Jean-Marie Philippe Hugues Chouard , Guillaume Lefort
IPC分类号： F02C7/20
CPC分类号： B64D27/26 , B64D2027/268
摘要： The present invention relates to an isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the same axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing. It is characterized in that the plane formed by the two links of the rear attachment is inclined with respect to the plane of the exhaust casing.
摘要翻译：技术领域本发明涉及一种用于将涡轮喷气发动机安装在飞机的塔架上的等静压悬架，该涡轮喷气发动机包括前风扇，具有外壳的风扇下游的中间壳体和通过径向臂互连的轮毂，以及排气壳体，其具有在相同轴线XX上的外壳，悬架包括在中间壳体上的前部附件，后部附件，其具有连接到排气壳体的外部壳体的至少两个后部附接链节，一对推杆固定在它们的上游端到达中间壳体的毂。其特征在于，由后附件的两个连杆形成的平面相对于排气套的平面倾斜。

5. 发明申请

US20110001002A1 SUSPENSION FOR MOUNTING A TURBOJET ENGINE ON AN AIRCRAFT 有权
标题翻译：用于在飞机上安装涡轮发动机的悬架
公开(公告)号：US20110001002A1
公开(公告)日：2011-01-06
申请号：US12329136
申请日：2008-12-05
申请人： Pierre-Alain Jean-Marie Philippe Hugues CHOUARD , Guillaume LEFORT
发明人： Pierre-Alain Jean-Marie Philippe Hugues CHOUARD , Guillaume LEFORT
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64D2027/268
摘要： The present invention relates to an isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the same axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing. It is characterized in that the plane formed by the two links of the rear attachment is inclined with respect to the plane of the exhaust casing.
摘要翻译：技术领域本发明涉及一种用于将涡轮喷气发动机安装在飞机的塔架上的等静压悬架，该涡轮喷气发动机包括前风扇，风扇下游的外壳和通过径向臂互连的轮毂和排气壳体，其具有在相同轴线XX上的外壳，悬架包括在中间壳体上的前部附件，后部附件，其具有连接到排气壳体的外部壳体的至少两个后部附接链节，一对推杆固定在它们的上游端到达中间壳体的毂。其特征在于，由后附件的两个连杆形成的平面相对于排气套的平面倾斜。

6. 发明申请

US20100008772A1 NACELLE FOR THE JET ENGINE OF AN AIRCRAFT 有权
标题翻译：用于飞机喷气发动机的NACELLE
公开(公告)号：US20100008772A1
公开(公告)日：2010-01-14
申请号：US12527086
申请日：2007-11-23
申请人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Pierre-Alain Chouard , Guillaume Lefort
发明人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Pierre-Alain Chouard , Guillaume Lefort
IPC分类号： F01D25/24
CPC分类号： B64D29/08 , F02K1/00 , F05D2230/80 , Y02T50/671
摘要： The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.
摘要翻译：本发明涉及一种用于涡轮喷气发动机的机舱，其类型包括具有外部结构（6）的下游结构，外部结构（6）与用于包围涡轮喷气发动机的下游部分的内部同心结构（9）一起限定，环形流动通道其特征在于，至少所述内部结构（9）的一部分被安装成能够沿着所述机舱的纵向轴线的平移运动，使得其能够在工作位置之间移动，其中所述内部结构用作涡轮喷气发动机的下游部分的壳体，以及内部结构暴露涡轮喷气发动机的所述下游部分的维护位置。

7. 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。

8. 发明申请

US20080067287A1 PROPULSION SYSTEM WITH INTEGRATED PYLON 有权
标题翻译：具有整体式PYLON的推进系统
公开(公告)号：US20080067287A1
公开(公告)日：2008-03-20
申请号：US11857735
申请日：2007-09-19
申请人： Thibaud Jean-Baptiste GUIBERT , Guillaume LEFORT , Marc Patrick TESNIERE
发明人： Thibaud Jean-Baptiste GUIBERT , Guillaume LEFORT , Marc Patrick TESNIERE
IPC分类号： B64D27/18
CPC分类号： B64D27/26 , B64D2027/264 , F01D25/28 , F02C7/20 , Y02T50/44 , Y02T50/671
摘要： Propulsion system with integrated pylon Propulsion system comprising a bypass turbojet and a nacelle (10) a downstream cylindrical part (20) of which is rigid and is attached at its upstream end to an intermediate case of the engine, this downstream cylindrical part (20) also comprising a longitudinal beam (26) for attaching rods (28) for securing the engine to part (22) of an airplane.
摘要翻译：具有集成塔架的推进系统包括旁通涡轮喷气发动机和机舱（10）的推进系统，其下游圆柱形部分（20）是刚性的并且在其上游端附接到发动机的中间壳体，该下游圆柱形部分（20）还包括用于连接用于将发动机固定到飞机的部分（22）的杆（28）的纵向梁（26）。

9. 发明授权

US08951006B2 Nacelle for the jet engine of an aircraft 有权
标题翻译：用于飞机喷气发动机的机舱
公开(公告)号：US08951006B2
公开(公告)日：2015-02-10
申请号：US12527086
申请日：2007-11-23
申请人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Pierre-Alain Chouard , Guillaume Lefort
发明人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Pierre-Alain Chouard , Guillaume Lefort
IPC分类号： F01D25/24 , B64D29/08 , F02K1/00
CPC分类号： B64D29/08 , F02K1/00 , F05D2230/80 , Y02T50/671
摘要： The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure (6) that defines, together with an inner concentric structure (9) for surrounding the downstream portion of the turbojet, an annular flow channel (8), characterised in that a portion at least of said inner structure (9) is mounted so as to be capable of a translation movement along the longitudinal axis of the nacelle so that it can move between a working position, in which the inner structure acts as a casing for the downstream portion of the turbojet, and a maintenance position in which the inner structure exposes said downstream portion of the turbojet.
摘要翻译：本发明涉及一种用于涡轮喷气发动机的机舱，其类型包括具有外部结构（6）的下游结构，外部结构（6）与用于包围涡轮喷气发动机的下游部分的内部同心结构（9）一起限定，环形流动通道其特征在于，至少所述内部结构（9）的一部分被安装成能够沿着所述机舱的纵向轴线的平移运动，使得其能够在工作位置之间移动，其中所述内部结构用作涡轮喷气发动机的下游部分的壳体，以及内部结构暴露涡轮喷气发动机的所述下游部分的维护位置。

10. 发明授权

US07938359B2 Propulsion system with integrated pylon 有权
标题翻译：集成塔式推进系统
公开(公告)号：US07938359B2
公开(公告)日：2011-05-10
申请号：US11857735
申请日：2007-09-19
申请人： Thibaud Jean-Baptiste Guibert , Guillaume Lefort , Marc Patrick Tesniere
发明人： Thibaud Jean-Baptiste Guibert , Guillaume Lefort , Marc Patrick Tesniere
IPC分类号： B64D27/00 , B64D27/26 , B64D29/06
CPC分类号： B64D27/26 , B64D2027/264 , F01D25/28 , F02C7/20 , Y02T50/44 , Y02T50/671
摘要： A propulsion system for an airplane having an integrated pylon includes a bypass turbojet and a nacelle. The nacelle has a downstream cylindrical part which is rigid and is attached at its upstream end to an intermediate case of the engine. This downstream cylindrical part also includes a longitudinal beam for attaching rods to secure the engine to the airplane.
摘要翻译：具有集成塔架的飞机的推进系统包括旁通涡轮喷气发动机和机舱。机舱具有刚性的下游圆柱形部分，并且在其上游端附接到发动机的中间壳体。该下游圆柱形部分还包括用于连接杆以将发动机固定到飞机的纵向梁。

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