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61. 发明申请

WO2009106763A3 TWELVE-HOUR STRUCTURE FOR THRUST REVERSER, IN PARTICULAR WITH GRIDS 审中-公开
标题翻译：推力反推器，特别是网格的十二小时结构
公开(公告)号：WO2009106763A3
公开(公告)日：2009-11-05
申请号：PCT/FR2009000023
申请日：2009-01-09
申请人： AIRCELLE SA , VACHE JEAN-BERNARD , VALLEROY LAURENT
发明人： VACHE JEAN-BERNARD , VALLEROY LAURENT
IPC分类号： B64D29/06 , F02K1/72
CPC分类号： F02K1/72 , B64C7/02 , B64D29/06 , F05D2220/36 , F05D2300/612 , Y02T50/672
摘要： The invention relates to a twelve-hour structure for a thrust reverser, that comprises a half beam (1) capable of holding a reverser half cowling and including a plurality of hinge yokes (9c) for rotatingly mounting said half beam (1) on a nacelle-holding mast. The half beam (1) is at least partially made of a composite material.
摘要翻译：本发明涉及一种用于推力反向器的十二小时结构，其包括能够保持反向器半罩并且包括多个铰链轭（9c）的半梁（1），所述铰链轭用于将所述半梁（1）旋转地安装在发动机舱控股桅杆。半梁（1）至少部分由复合材料制成。

62. 发明申请

WO2009077666A3 PIEZOELECTRIC DE-ICING OF AN AIR INLET 审中-公开
标题翻译：空气入口的压电断电
公开(公告)号：WO2009077666A3
公开(公告)日：2009-08-20
申请号：PCT/FR2008001353
申请日：2008-09-29
申请人： AIRCELLE SA , LE DOCTE THIERRY
发明人： LE DOCTE THIERRY
IPC分类号： B64D15/16
CPC分类号： B64D33/02 , B64D15/163 , B64D2033/0233
摘要： The invention relates to a lip assembly (1) for the air inlet of a turbojet engine nacelle, that comprises an inner surface (9), an outer surface (11) and de-icing means, wherein the de-icing means includes an anti-ice coating (13) covering at least a portion of the outer surface (11), said anti-ice coating (13) including one or more piezoelectric actuators within the matrix of said coating (13). The invention also relates to a turbojet engine nacelle that comprises such a lip assembly (1).
摘要翻译：本发明涉及一种用于涡轮喷气发动机机舱的空气入口的唇部组件（1），其包括内表面（9），外表面（11）和除冰装置，其中除冰装置包括防反射装置 - 覆盖所述外表面（11）的至少一部分的所述防冰涂层（13）包括在所述涂层（13）的基体内的一个或多个压电致动器。本发明还涉及一种包括这种唇形组件（1）的涡轮喷气发动机机舱。

63. 发明申请

WO2009024666A3 ACTUATOR FOR OPENING AN AIRCRAFT ENGINE NACELLE COWL 审中-公开
标题翻译：用于开启飞机发动机的执行器NACELLE COWL
公开(公告)号：WO2009024666A3
公开(公告)日：2009-06-25
申请号：PCT/FR2008000895
申请日：2008-06-25
申请人： AIRCELLE SA , MORADELL-CASELLAS PIERRE , LEDERLE STEPHANE
发明人： MORADELL-CASELLAS PIERRE , LEDERLE STEPHANE
IPC分类号： F15B15/26
CPC分类号： F15B15/148 , B64D29/06 , F15B15/261
摘要： Actuator (V) for opening an aircraft nacelle cowl (7), comprising a dead travel device (19), characterized in that it comprises means (42a, 42b, 43) for blocking the dead travel device (19) when this actuator (V) is extended.
摘要翻译：用于打开飞机机舱罩（7）的致动器（V），包括死区行程装置（19），其特征在于，其包括用于当所述致动器（V）的阻塞所述死行程装置（19）的装置（42a，42b，）被扩展。

64. 发明申请

WO2009060137A2 AIR INTAKE STRUCTURE TO BE MOUNTED UPSTREAM OF A NACELLE MIDDLE STRUCTURE FOR AIRCRAFT ENGINE, AND NACELLE EQUIPPED WITH SUCH AIR INTAKE STRUCTURE 审中-公开
标题翻译：用于飞机发动机的空调中间结构的空气入口结构和装有这种空气吸入结构的空调
公开(公告)号：WO2009060137A2
公开(公告)日：2009-05-14
申请号：PCT/FR2008001208
申请日：2008-08-28
申请人： AIRCELLE SA , VAUCHEL GUY BERNARD , BEILLIARD STEPHANE , DAUGUET JEAN-PHILIPPE
发明人： VAUCHEL GUY BERNARD , BEILLIARD STEPHANE , DAUGUET JEAN-PHILIPPE
IPC分类号： B64D15/04 , B64D33/02 , F02C7/047
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0233 , F02C7/047 , Y02T50/671
摘要： The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall (7) including a lip (9) and that can be mounted relative to said middle structure so as to move between a rear position and a front position; a wall (11) defining a de-icing compartment (13) in said lip (9); at least one de-icing collector (15) extending in said compartment (13); and at least one hot-air supply duct (17) of said collector (15), that can be rigidly connected to said middle structure. The wall (11) is tightly secured inside said lip (9), and said supply duct (17) is connected to said collector (15) by removable sealing means (27, 29, 31, 35).
摘要翻译：本发明涉及一种可以安装在用于飞行器发动机的机舱中间结构的上游的进气结构，并且特别地包括：包括唇缘（9）的外壁（7），并且可以相对于所述中间结构以便在后部位置和前部位置之间移动; 在所述唇缘（9）中限定除冰隔间（13）的壁（11）; 在所述隔室（13）中延伸的至少一个除冰收集器（15）; 以及所述收集器（15）的至少一个热风供应管道（17），其可以刚性地连接到所述中间结构。壁（11）紧密地固定在所述唇部（9）内，并且所述供应管道（17）通过可移除的密封装置（27,29,31,35）连接到所述收集器（15）。

65. 发明申请

WO2008139048A3 NACELLE FOR TURBOJET JET FITTED WITH A SINGLE DOOR THRUST REVERSER SYSTEM 审中-公开
标题翻译：用于单壁门扭转系统的涡轮喷嘴的NACELLE
公开(公告)号：WO2008139048A3
公开(公告)日：2009-01-29
申请号：PCT/FR2008000454
申请日：2008-04-02
申请人： AIRCELLE SA , D INCA ALAIN , THIERRY MARTIN
发明人： D INCA ALAIN , MARTIN THIERRY
IPC分类号： F02K1/58 , F02K1/60
CPC分类号： F02K1/58 , F02K1/60 , Y02T50/671
摘要： Nacelle (1) for a turbojet including an air intake structure capable of directing the air flow towards a turbojet fan, a middle structure for surrounding said fan and a downstream section (10) provided with a pivotal-door thrust reverser system including a single thrust reversal door (17) pivotally mounted between a closing position, in which it allows the circulation of an air flow of the turbojet as a direct jet and in which it ensures the inner and outer aerodynamic continuity of the nacelle, and an opening position in which it can pivot to a position substantially perpendicular to the nacelle axis, a downstream portion (17a) of said door penetrating inside the nacelle for at least partially blocking a portion of the turbojet air flow and directing the same in a direction towards the front of the nacelle, characterised in that the downstream section (10) includes, downstream from the door (17), a ring extending on the entire periphery thereof.
摘要翻译：一种用于涡轮喷气发动机的机舱（1），其包括能够将空气流引向涡轮喷气风扇的进气结构，用于围绕所述风扇的中间结构和设置有包括单推力的枢转门推力反向器系统的下游部分（10）反转门（17）枢转地安装在关闭位置之间，其中允许涡轮喷气发动机的空气流作为直接喷射器循环，并且其中确保机舱的内部和外部空气动力学连续性，以及打开位置，它可以枢转到基本上垂直于机舱轴线的位置，所述门的下游部分（17a）穿过机舱内部，以至少部分地阻挡涡轮喷气式空气流的一部分并将其引向朝向前方的方向其特征在于，所述下游部分（10）在所述门（17）的下游包括在其整个周边上延伸的环。

66. 发明申请

WO2011151577A3 TURBOJET ENGINE NACELLE INCLUDING A DEVICE FOR ABSORBING CIRCUMFERENTIAL STRESSES 审中-公开
标题翻译：涡轮发动机包括用于吸收循环应力的装置
公开(公告)号：WO2011151577A3
公开(公告)日：2012-09-13
申请号：PCT/FR2011051212
申请日：2011-05-27
申请人： AIRCELLE SA , JORET JEAN-PHILIPPE , SEGAT PETER , VAUCHEL GUY BERNARD , BOURET GEORGES ALAIN
发明人： JORET JEAN-PHILIPPE , SEGAT PETER , VAUCHEL GUY BERNARD , BOURET GEORGES ALAIN
IPC分类号： B64D29/06
CPC分类号： F02K1/70 , B64D29/06 , F02K1/766
摘要： The invention relates to a nacelle (1) for an aircraft turbojet engine, comprising: a fan casing secured to a supporting pylon and surrounded by an outer fan cowl; an internal structure; a thrust reverser (50) comprising two removable half-cowls (51) hinged to the pylon along hinge lines (LC); and a device (6; 7; 8; 9; 10) for absorbing circumferential stresses connecting the upper edges (52) of the half-cowls (51) under the upstream portion of the pylon (2), said stress-absorbing device being disposed between the external line of an annular channel and the hinge lines (LC). The stress-absorbing device is shaped to: (i) lock the half-cowls (51) in the closed position when in a locking configuration, and (ii) allow the half-cowls (51) to be opened when in an unlocking configuration. In addition, said device is only attached to the half-cowls, such that the half-cowls can be opened independently of the opening/closing of the external fan cowl.
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（1），包括：风扇壳体，其固定到支撑塔并被外部风扇罩包围; 内部结构; 推力反向器（50），包括沿铰链线（LC）铰接到塔架的两个可拆卸半罩（51）; 以及用于吸收将所述半罩（51）的上边缘（52）连接在所述塔（2）的上游部分的周向应力的装置（6; 7; 8; 9; 10），所述应力吸收装置设置在环形通道的外线和铰链线（LC）之间。所述应力吸收装置的形状为：（i）当处于锁定构型时，所述半罩（51）处于关闭位置，并且（ii）当处于解锁构造时允许半罩（51）打开。另外，所述装置仅与半罩相连，使得半罩可独立于外部风扇罩的打开/关闭而打开。

67. 发明申请

WO2012085156A2 METHOD FOR BRAIDING REINFORCING FIBRES WITH VARIATION IN THE INCLINATION OF THE BRAIDED FIBRES 审中-公开
标题翻译：用于在布线纤维包裹中改变增强纤维的方法
公开(公告)号：WO2012085156A2
公开(公告)日：2012-06-28
申请号：PCT/EP2011073692
申请日：2011-12-21
申请人： MESSIER BUGATTI DOWTY , AIRCELLE SA , MASSON RICHARD , DESJOYEAUX BERTRAND , BOUDIER ROMAIN
发明人： MASSON RICHARD , DESJOYEAUX BERTRAND , BOUDIER ROMAIN
IPC分类号： D04C1/06 , B29C70/24 , B29C70/30 , D04C1/02 , D04C3/00 , D04C3/34 , F16C7/00
CPC分类号： D04C1/06 , D04C3/34 , D04C3/48 , D10B2505/02
摘要： The invention relates to a method for braiding reinforcing fibres on a mandrel (8) using a machine comprising a ring (9) carrying at least two series of spools of fibres, by moving this mandrel at a predetermined feed rate and by moving the two series of spools along the ring (9) so that they crisscross by rotating in opposite directions at a predetermined speed of rotation about an axis (AX) of this ring, the braid being formed on the mandrel (8) at a region of convergence (R) of the fibres which together delimit a conical shape (C), characterized in that it comprises: a step of reconfiguring the machine in which the angle (a2) at the vertex of the cone (C) delimited by the fibres adopts a new value (a2); a step of resuming braiding in which the movement of the spools along the ring (9) and the feed rate of the mandrel (8) are re-established at a new feed rate and a new rotational speed.
摘要翻译：本发明涉及一种用于使用机器将增强纤维编织在心轴（8）上的方法，所述机器包括通过以预定的进给速率移动该心轴并且通过移动两个系列来携带至少两系列的纤维卷轴的环（9）沿着环（9）的线轴旋转，使得它们以相对于该环的轴线（AX）的预定旋转速度以相反方向旋转，编织物在会聚区域（R ），其一起限定圆锥形（C），其特征在于，其包括：重新配置机器的步骤，其中由纤维限定的锥体（C）的顶点处的角度（a2）采用新值（a2）; 重新开始编织的步骤，其中以新的进给速率和新的转速重新建立沿着环（9）的线轴的运动和心轴（8）的进给速率。

68. 发明申请

WO2012059677A2 AIRCRAFT TURBOJET ENGINE THRUST REVERSER WITH A LOWER NUMBER OF ACTUATORS 审中-公开
标题翻译：飞机涡轮发动机用较少数量的执行机构反相
公开(公告)号：WO2012059677A2
公开(公告)日：2012-05-10
申请号：PCT/FR2011052544
申请日：2011-10-28
申请人： AIRCELLE SA , KERBLER OLIVIER , DEZEUSTRE NICOLAS , HURLIN HERVE
发明人： KERBLER OLIVIER , DEZEUSTRE NICOLAS , HURLIN HERVE
IPC分类号： F02K1/72 , F02K1/76 , F02K1/80
CPC分类号： F02K1/566 , F02K1/72 , F02K1/763 , Y02T50/671
摘要： This cascade-type thrust reverser with one-piece moving cowl (23) comprises rails able to slide in guideways positioned on each side of a suspension pylon (8). This thrust reverser comprises just two actuators (43a, 43b) positioned near said rails and able to cause this cowl (23) to slide on said guideways between its direct-jet and reverse-jet positions. It also comprises means capable of compensating for forces that have a tendency to misalign said rails with respect to said guideways, thus preventing them from jamming in one another.
摘要翻译：这种具有单件式移动整流罩（23）的级联式推力反向器包括能够在位于悬挂塔（8）的每一侧的导轨中滑动的轨道。该推力反向器仅包括位于所述轨道附近的两个致动器（43a，43b），并且能够使得整流罩（23）在其直接喷射和反向喷射位置之间的所述导轨上滑动。它还包括能够补偿具有相对于所述导轨对准所述轨道的倾向的力的装置，从而防止它们彼此卡住。

69. 发明申请

WO2011072846A3 METHODS FOR PRODUCING A PART MADE FROM A COMPOSITE MATERIAL, OBTAINED BY DEPOSITING LAYERS OF REINFORCING FIBERS URGED ONTO A MANDREL 审中-公开
标题翻译：用于生产由复合材料制成的部件的方法，通过将加强在纤维上的纤维层沉积成层
公开(公告)号：WO2011072846A3
公开(公告)日：2011-09-01
申请号：PCT/EP2010007659
申请日：2010-12-16
申请人： MESSIER BUGATTI DOWTY , AIRCELLE SA , MASSON RICHARD , DUNLEAVY PATRICK , DESJOYEAUX BERTRAND
发明人： MASSON RICHARD , DUNLEAVY PATRICK , DESJOYEAUX BERTRAND
IPC分类号： B29C70/32 , B29C53/56 , B29C70/54
CPC分类号： B29C70/32 , B29C53/566 , B29C53/70 , B29C53/8083 , B29C70/222 , B29C70/48 , B29C70/543 , B29K2307/00 , B29L2023/22
摘要： The invention relates to a method for producing a part made from a composite material, wherein one or more layers (17) of braided or woven or even draped reinforcing fibers (4) are applied to a mandrel having an overall rotationally symmetrical shape. After one or more layers (17) have been applied to the mandrel (2), a compacting operation is carried out either using at least one tie (7), which is helically wound around and along the assembly (6) consisting of the mandrel (2) and each layer (17) of reinforcing fibers (4) that said mandrel supports, or using equipment comprising a frame rotating about the mandrel and bearing an urging member that is applied at least partially radially against the assembly formed by the mandrel (2) and each layer (17, 18) borne thereby.
摘要翻译：本发明涉及一种用于制造由复合材料制成的零件的方法，其中编织或编织或均匀覆盖的增强纤维（4）的一个或多个层（17）施加到具有整体旋转对称形状的心轴。在将一个或多个层（17）施加到心轴（2）之后，使用至少一个连接件（7）进行压实操作，该连接件（7）螺旋缠绕在组合件（6）周围并且沿着由心轴（2）和所述心轴支撑的增强纤维（4）的每个层（17），或者使用包括围绕心轴旋转的框架的设备，并且承载施加构件，该施力构件至少部分径向地抵靠由心轴形成的组件 2）和由此承载的每个层（17,18）。

70. 发明申请

WO2010061071A3 NACELLE INTEGRATED ON A FLYING WING 审中-公开
标题翻译： NACELLE集成在飞翼上
公开(公告)号：WO2010061071A3
公开(公告)日：2010-10-07
申请号：PCT/FR2009001305
申请日：2009-11-13
申请人： AIRCELLE SA , VAUCHEL GUY BERNARD
发明人： VAUCHEL GUY BERNARD
IPC分类号： B64C39/10 , B64D27/18 , B64D29/02 , B64D29/08
CPC分类号： B64C39/10 , B64C2039/105 , B64D27/20 , B64D2033/022 , B64D2033/0286 , Y02T50/12
摘要： The invention relates to a nacelle (23) for a turbojet engine (21), comprising an air intake structure (25) capable of directing an air flow towards a fan (27) of a turbojet engine (21), a middle structure (29) for surrounding said fan (27) and to which the air intake structure (25) is secured so as to provide aerodynamic continuity, and a downstream section (31) to which the middle structure (29) is attached, characterised in that the air intake structure (25) is adapted so as to define a continuous extension of the walls (33; 34) of a flying wing (3) so that the air intake structure (25), the middle structure (29), and the downstream structure (31) are in aerodynamic continuity with the flying wing (3). The invention also relates to a flying wing (3) and to an aircraft (1) comprising such a nacelle.
摘要翻译：本发明涉及一种用于涡轮喷气发动机（21）的机舱（23），其包括能够将空气流导向涡轮喷气发动机（21）的风扇（27）的进气结构（25），中间结构），用于围绕所述风扇（27）并且所述进气结构（25）被固定到所述风扇以提供空气动力学连续性;以及下游部分（31），所述中间结构（29）被附接到所述下游部分（31），其特征在于，进气结构（25）适于限定飞翼（3）的壁（33; 34）的连续延伸部分，使得进气结构（25），中间结构（29）和下游结构（31）与飞翼（3）处于空气动力学连续性。本发明还涉及一种飞翼（3）以及包括这种机舱的飞机（1）。

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