公开(公告)号：US08333343B2

公开(公告)日：2012-12-18

申请号：US12674192

申请日：2008-06-12

申请人： Gilles Bourdon

发明人： Gilles Bourdon

IPC分类号： B64D33/02 ,  B64D29/00 ,  B64B1/24

CPC分类号： B64D29/08 ,  Y10T137/0536

摘要： The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second half-shells (9, 10) rotatably mounted about an axis (A) such that they can each be deployed between a working position in which the half-shells (9, 10) are drawn towards one another and a maintenance position in which the half-shells (9, 10) are spaced apart, the mid- and aft sections being connected to one another by a frame (12) which is fixed with respect to the jet engine, the first and second half-shells (9, 10) being equipped with positioning means (13) which in the working position cooperate with complementary positioning means (14) formed on the fixed frame (12). At least the first half-shell (10) is equipped with the locking means (20) which in the maintenance position cooperate with complementary locking means (16, 17) arranged on the fixed frame (12), so as to prevent the first half-shell (10) from moving translationally along its axis (A).

摘要翻译： 本发明涉及一种旨在装备飞行器的喷气发动机机舱，包括前进气进口部分，用于围绕喷气发动机的风扇的中间部分以及由至少第一和第二半壳形成的后部（ 9，10）围绕轴线（A）可旋转地安装，使得它们可以各自部署在半壳（9,10）彼此相对的工作位置和维持位置之间，半壳 9,10）间隔开，中间和后部通过相对于喷气发动机固定的框架（12）彼此连接，第一和第二半壳（9,10）装备有 定位装置（13）在工作位置与形成在固定框架（12）上的互补定位装置（14）配合。 至少第一半壳（10）配备有锁定装置（20），其在维护位置与布置在固定框架（12）上的互补锁定装置（16,17）配合，以防止前半部 - 壳（10）沿其轴线（A）平移运动。

公开(公告)号：US08181912B2

公开(公告)日：2012-05-22

申请号：US12454922

申请日：2009-05-26

申请人： Detlev Schwetzler

发明人： Detlev Schwetzler

IPC分类号： B64C23/06 ,  B64D29/00

CPC分类号： B64C23/06 ,  B64C7/02 ,  B64D29/02 ,  Y02T50/162

摘要： An engine pod for an aircraft has one side which features several fin-shaped vortex generators such that the overall vorticity field generated by the vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases. The first vortex generator lies within a positioning corridor that is situated between two boundary lines. The origin and end points, respectively, of the first boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and 25 degrees and the longitudinal engine pod coordinate X=L/4 and L·⅔. The origin and end points, respectively, of the second boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=90 degrees and 55 degrees and the longitudinal engine pod coordinate X=L/4 and L·⅔.

摘要翻译： 用于飞行器的发动机舱具有一侧，其特征在于具有若干鳍形涡流发生器，使得涡流发生器产生的整体涡度场随着迎角增加而在翼展方向上延伸越过翼型面积。 第一个涡流发生器位于两条边界线之间的定位走廊内。 第一边界线的起点和终点分别是发动机舱的圆周上的点，圆周发动机舱角度为35度和25度，纵向发动机舱座标X = L / 4和L· ⅔。 第二边界线的起点和终点分别是发动机舱的圆周上的点，圆周发动机舱角度φi= 90度和55度，纵向发动机舱座标X = L / 4和L· ⅔。

公开(公告)号：US20110250054A1

公开(公告)日：2011-10-13

申请号：US12673868

申请日：2008-07-16

申请人： David Pereira

发明人： David Pereira

IPC分类号： B64D29/00 ,  B64D29/08 ,  B64D29/02 ,  B64F5/00

CPC分类号： B64D29/08 ,  Y10T307/76

摘要： The invention relates to a device (9) for controlling the maintenance actuators (7a, 7b) of the cowlings of a turbojet engine nacelle of an aircraft, that comprises a first stage (12) to be connected to an electric power network (10) of the aircraft, at least one second power stage (13a, 13b) including converters of a first DC voltage from the first stage (12) into a second DC voltage for powering at least one maintenance actuator (7a, 7b) connected downstream from the device (9), a control means (14) for the first and second stages (12, 13a, 13b), and a means (15) for establishing a communication between the control means (14) and at least one control housing (16a, 16b) so that a user can control the operation of the actuators, the control means being arranged so as to carry out switching operations between a first operation mode in which the second stage(s) (13a, 13b) are powered, and a second standby mode in which the second stage(s) (13a, 13b) are not powered by the first stage (12).

摘要翻译： 本发明涉及一种用于控制飞机的涡轮喷气发动机机舱的整流罩的维护致动器（7a，7b）的装置（9），其包括要连接到电力网络（10）的第一级（12） 所述至少一个第二功率级（13a，13b）包括从所述第一级（12）的第一DC电压的转换器转换成用于为至少一个维护致动器（7a，7b）供电的第二DC电压，所述维护致动器 装置（9），用于第一和第二级（12,13a，13b）的控制装置（14）和用于在控制装置（14）和至少一个控制壳体（16a）之间建立连通的装置 ，16b），使得用户可以控制致动器的操作，控制装置被布置成在第二级（13a，13b）被供电的第一操作模式和 第二待机模式，其中第二级（13a，13b）不由第一级（12）供电 ）。

公开(公告)号：US20100284806A1

公开(公告)日：2010-11-11

申请号：US12446733

申请日：2007-09-14

申请人： Guy Bernard Vauchel ,  Xavier Cazuc

发明人： Guy Bernard Vauchel ,  Xavier Cazuc

IPC分类号： F01D25/24 ,  B64D29/00

CPC分类号： B64D29/08 ,  B64D29/06

摘要： The invention relates to a nacelle including an air intake upstream from the jet engine (1), a medium section surrounding the fan of the jet engine (1), and a downstream section. The nacelle further includes at least one pair of mobile cowlings (3) provided on both sides of a vertical longitudinal symmetry plane of the nacelle and hinged essentially parallel to a longitudinal axis (A) of the nacelle so they can be opened to provide access to the jet engine (1). The mobile cowlings (3) are paired by fastening means (8) so that they can be hinged on each other about separate or overlapping axes (6). Each mobile cowling (3) comprises permanent connection means or means (14, 15) for connecting it temporarily by rotation and in closed position to a fixed structure (7) of the nacelle.

摘要翻译： 本发明涉及一种机舱，其包括从喷气发动机（1）上游的进气口，围绕喷气发动机（1）的风扇的介质部分和下游部分。 机舱还包括至少一对移动整流罩（3），其设置在机舱的垂直纵向对称平面的两侧并且基本上平行于机舱的纵向轴线（A）铰接，使得它们可以被打开以提供通向 喷气发动机（1）。 移动整流罩（3）通过紧固装置（8）配对，使得它们可以围绕分开的或重叠的轴线（6）彼此铰接。 每个移动整流罩（3）包括永久性连接装置或装置（14,15），用于通过旋转和关闭位置临时地连接到机舱的固定结构（7）。

公开(公告)号：US07703716B2

公开(公告)日：2010-04-27

申请号：US11798375

申请日：2007-05-14

申请人： Guillaume Bulin

发明人： Guillaume Bulin

IPC分类号： B64D29/00 ,  B64D29/08

CPC分类号： B64D29/06 ,  B64D29/08

摘要： A hinged device for at least one door (46.1, 46.2) of an aircraft nacelle (40), whereby the door is able to block an opening (44) that is made in the fairing of the nacelle, the device including a base to which is connected at least one door, able to occupy a first retracted state in which the base is located at least in part inside the nacelle and a second extended state in which the base is located outside the fairing of the nacelle so as to be able to move, in a direction that is essentially parallel to the longitudinal axis of the nacelle, outside of the nacelle by entraining the at least one door (46.1, 46.2) to release the opening (44) at least in part.

摘要翻译： 一种用于飞机机舱（40）的至少一个门（46.1,46.2）的铰接装置，由此门能够阻挡在机舱的整流罩中制造的开口（44），该装置包括基座 连接至少一个门，其能够占据第一缩回状态，其中基座至少部分地位于机舱内部;第二延伸状态，其中基座位于机舱的整流罩之外，以便能够 在基本上平行于所述机舱的纵向轴线的方向上，通过夹带所述至少一个门（46.1,46.2）至少部分地释放所述开口（44）而在所述机舱的外部移动。

公开(公告)号：US20090084889A1

公开(公告)日：2009-04-02

申请号：US12178704

申请日：2008-07-24

申请人： Olivier Cazals ,  Alexander Koch

发明人： Olivier Cazals ,  Alexander Koch

IPC分类号： B64C11/00 ,  B64D27/00 ,  B64D33/02 ,  B64D29/00

CPC分类号： B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  B64D29/04 ,  B64D29/08 ,  B64D33/02 ,  B64D33/06 ,  B64D2033/0286 ,  Y02T50/44

摘要： An aircraft the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following, air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

摘要翻译： 包括引擎在内的推进单元的飞机包括固定在机身上部区域的机翼结构以及具有至少两个垂直稳定器的垂直尾翼系统，该垂直尾翼系统通常垂直地固定在机身上 机身后部的机身结构。 发动机并排布置在设置在机身上方的推进式包装中，该推进包装包括用于推进包装的以下空气入口，这些开口设置在机身的上方，位于前缘的一点和 机翼结构的气动根弦的后缘; 以及与排气喷嘴管道相关联的排气喷嘴导管出口，这些出口由推进式包装的结构（整流罩结构）形成，并且设置在机身的后端的机身前方和垂直稳定器之间。

公开(公告)号：US20060038064A1

公开(公告)日：2006-02-23

申请号：US11075851

申请日：2005-03-10

申请人： Emmanuel Mandet ,  Jacques-A Roche ,  Laurent Salperwyck

发明人： Emmanuel Mandet ,  Jacques-A Roche ,  Laurent Salperwyck

IPC分类号： B64D33/00 ,  B64D29/00

CPC分类号： F01D25/24 ,  F02C7/20 ,  F02K1/822 ,  F05D2230/642 ,  Y02T50/675

摘要： The bridge piece makes it possible to limit mechanical stresses in the heat shield liner and the nozzle support pipe envelope. According to the invention, it comprises a central part with inversed curvature (3) thus having two contact zones (4) with the nozzle support pipe envelope (2). Furthermore, one of the two lugs (5B) is mounted sliding in the heat shield liner (1). Application to turboprops with cooling bypass air flow.

摘要翻译： 桥接件可以限制隔热衬套和喷嘴支撑管外壳中的机械应力。 根据本发明，它包括具有反转曲率（3）的中心部分，因此具有带有喷嘴支撑管壳（2）的两个接触区（4）。 此外，两个凸耳（5B）中的一个安装在隔热衬套（1）中滑动。 应用于具有冷却旁路气流的涡轮螺旋桨发动机。

公开(公告)号：US20050045774A1

公开(公告)日：2005-03-03

申请号：US10878513

申请日：2004-06-29

申请人： Barry Hocking

发明人： Barry Hocking

IPC分类号： B64C21/06 ,  B64D29/00

CPC分类号： B64D29/00 ,  B64C21/06 ,  B64C2230/04 ,  B64C2230/22 ,  B64D2033/0226 ,  Y02T50/166

摘要： A laminar flow nacelle for an aircraft engine, the nacelle having an outer member defining an aerodynamic shape for a fluid, an inner member defining a chamber with the outer member, and an inlet pipe fluidly connecting ambient air with the chamber for ventilation thereof, the nacelle comprises a porous region at a first region of the outer member, the porous region arranged to allow a flow of fluid into a duct, characterised in that the inlet pipe comprises a venturi portion having a narrow low pressure part and the duct is connected to the narrow part to provide suction to the porous region.

摘要翻译： 一种用于飞机发动机的层流机舱，所述机舱具有限定用于流体的空气动力学形状的外部构件，限定具有外部构件的室的内部构件和将环境空气与所述室流体连接以便通风的入口管， 所述机舱包括在所述外部构件的第一区域处的多孔区域，所述多孔区域布置成允许流体流入管道，其特征在于，所述入口管道包括具有窄的低压部分的文氏管部分，并且所述管道连接到 该狭窄部分为多孔区域提供吸力。

公开(公告)号：US6131855A

公开(公告)日：2000-10-17

申请号：US203377

申请日：1998-12-02

申请人： Alain Porte

发明人： Alain Porte

IPC分类号： B64D15/04 ,  B64D29/00 ,  F02C7/047 ,  B64D15/00

CPC分类号： B64D29/00 ,  B64D15/04 ,  F02C7/047 ,  B64D2033/0233 ,  Y02T50/672

摘要： The present invention relates to an air inlet cowl (9) for a jet engine. According to the invention, provided in the partition (20) delimiting the de-icing chamber (21) in the hollow leading edge (16) of the cowl is a trough-shaped duct (22) for ejecting to the outside pressurized hot air which has flowed through the chamber (21). The duct (22) is reduced in cross section by a single oblong orifice (18) made, parallel to the leading edge (16), in a part (23) that forms part of the external surface (9E) of the cowl (9).

摘要翻译： 本发明涉及一种用于喷气发动机的进气罩（9）。 根据本发明，在整流罩的空心前缘（16）中限定了除冰室（21）的隔板（20）中设有用于向外部加压热空气喷射的槽形管道（22） 已经流过腔室（21）。 导管（22）的横截面通过与形成平行于前缘（16）的单个长方形孔（18）在部分（23）中减小，该部分构成整流罩（9）的外表面（9E）的一部分 ）。

公开(公告)号：US6129311A

公开(公告)日：2000-10-10

申请号：US13993

申请日：1998-01-27

申请人： John M. Welch ,  William E. Benton ,  Michael R. Lobsinger

发明人： John M. Welch ,  William E. Benton ,  Michael R. Lobsinger

IPC分类号： B29C70/34 ,  B29C70/86 ,  B29D24/00 ,  B29D99/00 ,  B64D29/00 ,  B64D29/02

CPC分类号： B29C70/865 ,  B29C70/342 ,  B29D24/007 ,  B29D99/0089 ,  B64D29/00 ,  B64D29/02 ,  B29K2995/0087 ,  B29L2031/3076 ,  B64D2033/0206

摘要： An outer cowl panel (24) for an engine nacelle (20). The outer cowl panel (24) includes integral track fairings (30) at aft side edges of the outer cowl panel. The outer cowl panel (24) also includes a chamfered leading edge having outer face sheets (88A, 88B) that extend over the leading edges of a stepped stack of prepreg sheets (88C, 88D, 88E, 88F).

摘要翻译： 一种用于发动机舱（20）的外罩（24）。 外罩面板（24）在外罩板的后侧边缘处包括整体的轨道整流罩（30）。 外罩面板（24）还包括具有外表面片（88A，88B）的倒角前缘，其延伸超过阶梯式叠层预浸片（88C，88D，88E，88F）的前缘。