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1. 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）。

2. 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。

3. 发明授权

US09156566B2 Securing plate and longitudinal handling member for a one-piece aircraft propulsion unit 有权
标题翻译：固定用于单件飞机推进装置的板和纵向处理构件
公开(公告)号：US09156566B2
公开(公告)日：2015-10-13
申请号：US12666122
申请日：2008-06-02
申请人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Jean-Francois Cribelier
发明人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Jean-Francois Cribelier
IPC分类号： B64F5/00 , B64D27/18 , B64D27/26
CPC分类号： B64F5/0036 , B64D27/18 , B64D27/26 , B64F5/50
摘要： The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing, second connection means (24) for securing the one-piece propulsion unit to the plate and third connection means (7) for securing a pair of longitudinal handling members (22) to the plate. The invention also relates to a specific longitudinal member and to an installation including a one-piece propulsion unit secured in the plate.
摘要翻译：本发明涉及一种用于将一体式推进单元（17）可移除地固定到飞机机翼的固定板（1），其特征在于，它包括用于固定的第一连接装置（4,5,8,13,14）板的板，用于将一体式推进单元固定到板的第二连接装置（24）和用于将一对纵向处理构件（22）固定到板上的第三连接装置（7）。本发明还涉及特定的纵向构件和包括固定在板中的一体式推进单元的装置。

4. 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。

5. 发明授权

US08528857B2 Translatable jet engine thrust reverser configuration providing improved maintenance access 失效
标题翻译：可翻译的喷气发动机推力反向器配置提供了改进的维修通道
公开(公告)号：US08528857B2
公开(公告)日：2013-09-10
申请号：US12517299
申请日：2007-11-19
申请人： Nicolas Hillereau , Jerome Collier , Guy Bernard Vauchel
发明人： Nicolas Hillereau , Jerome Collier , Guy Bernard Vauchel
IPC分类号： F02K1/54
CPC分类号： F02K1/72 , B64D29/06 , F02K1/766 , F02K1/80 , F05D2230/80 , F05D2240/14 , Y02T50/671
摘要： A translatable thrust inverter with grids for a turbojet, that defines at least a portion of the downstream section of a nacelle housing the turbojet. The thrust reversal system includes a front frame secured to a fixed portion of the nacelle and bearing. A first side includes cylinders for the translational actuation of at least one mobile cowling. A second side includes grids for inverting the peripheral thrusts, wherein the front frame includes a fixed portion for securing the front frame to the fixed portion of the nacelle and bearing the diversion grids. The system further includes a portion mounted so as to be capable of translational movement along the longitudinal axis of the nacelle and on which one end of the cowling actuation cylinders is attached, wherein the fixed and mobile portions of the front frame can be removably connected to each other by locking means.
摘要翻译：一种具有用于涡轮喷气发动机的网格的可翻转推力逆变器，其限定容纳涡轮喷气发动机的机舱的下游部分的至少一部分。推力反转系统包括固定到机舱和轴承的固定部分的前框架。第一侧包括用于至少一个移动整流罩的平移致动的气缸。第二侧包括用于反转周向推力的格栅，其中前框架包括固定部分，用于将前框架固定到机舱的固定部分并承载转向网格。该系统还包括安装成能够沿着机舱的纵向轴线平移运动并且其上安装有整流罩驱动气缸的一端的部分，其中前框架的固定和可移动部分可拆卸地连接到彼此通过锁定装置。

6. 发明申请

US20100181418A1 SECURING PLATE AND LONGITUDINAL HANDLING MEMBER FOR A ONE-PIECE AIRCRAFT PROPULSION UNIT 有权
标题翻译：一级飞机推进装置的安全板和纵向处理装置
公开(公告)号：US20100181418A1
公开(公告)日：2010-07-22
申请号：US12666122
申请日：2008-06-02
申请人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Jean-Francois Cribelier
发明人： Guy Bernard Vauchel , Nicolas Hillereau , Jerome Collier , Jean-Francois Cribelier
IPC分类号： B64D27/26
CPC分类号： B64F5/0036 , B64D27/18 , B64D27/26 , B64F5/50
摘要： The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing, second connection means (24) for securing the one-piece propulsion unit to the plate and third connection means (7) for securing a pair of longitudinal handling members (22) to the plate. The invention also relates to a specific longitudinal member and to an installation including a one-piece propulsion unit secured in the plate.
摘要翻译：本发明涉及一种用于将单件式推进单元（17）可拆卸地固定到飞行器机翼的固定板（1），其特征在于，它包括用于固定的第一连接装置（4,5,8,13,14）板的板，用于将一体式推进单元固定到板的第二连接装置（24）和用于将一对纵向处理构件（22）固定到板上的第三连接装置（7）。本发明还涉及特定的纵向构件和包括固定在板中的一体式推进单元的装置。

7. 发明申请

US20100040466A1 BYPASS TURBOJET ENGINE NACELLE 失效
标题翻译：旁路涡轮发动机NACELLE
公开(公告)号：US20100040466A1
公开(公告)日：2010-02-18
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： F01D25/28 , F16M13/00 , F02K3/02
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）。

8. 发明申请

US20100001123A1 TRANSLATABLE THRUST INVERTER FOR JET ENGINE 失效
标题翻译：用于喷气发动机的可翻转扭矩变送器
公开(公告)号：US20100001123A1
公开(公告)日：2010-01-07
申请号：US12517299
申请日：2007-11-19
申请人： Nicolas Hillereau , Jerome Collier , Guy Bernard Vauchel
发明人： Nicolas Hillereau , Jerome Collier , Guy Bernard Vauchel
IPC分类号： B64D29/06 , F02K1/72 , F02K1/76
CPC分类号： F02K1/72 , B64D29/06 , F02K1/766 , F02K1/80 , F05D2230/80 , F05D2240/14 , Y02T50/671
摘要： The invention relates to a thrust inverter with grids (5) for a turbojet, that defines at least a portion of the downstream section (103) of a nacelle (100) housing the turbojet, comprising a front frame (105) to be secured to a fixed portion (102) of the nacelle and bearing, on the one side, cylinders (6) for the translational actuation of at least one mobile cowling (2) and, on the other side, grids for inverting the peripheral thrusts, characterised in that the front frame includes a fixed portion for securing the front frame to the fixed portion of the nacelle and bearing the diversion grids, and a portion mounted so as to be capable of translation movement along the longitudinal axis of the nacelle and on which one end of the cowling actuation cylinders is attached, wherein the fixed and mobile portions of the front frame can be removably connected to each other by locking means.
摘要翻译：本发明涉及一种具有用于涡轮喷气发动机的格栅（5）的推力逆变器，其限定容纳涡轮喷气发动机的机舱（100）的下游部分（103）的至少一部分，包括前框架（105），以固定到在一侧的机舱和轴承的固定部分（102），一侧包括用于至少一个可移动整流罩（2）的平移致动的气缸（6），另一侧用于反转外围推力的网格，其特征在于前框架包括用于将前框架固定到机舱的固定部分并且承载转向栅格的固定部分，以及安装成能够沿着机舱的纵向轴线平移运动的部分，并且其一端安装整流罩致动气缸，其中前框架的固定和可移动部分可以通过锁定装置可拆卸地彼此连接。

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