公开(公告)号：US20040140397A1

公开(公告)日：2004-07-22

申请号：US10351159

申请日：2003-01-22

发明人： Roy Dun

IPC分类号： B64D027/00

CPC分类号： B64C7/02 ,  B64D33/04 ,  F02K1/44 ,  F02K1/52 ,  Y02T50/671

摘要： A scarf nozzle for a jet engine supported within a nacelle. The scarf nozzle is at an aft end of the nacelle. The scarf nozzle includes a first trailing edge portion and a second trailing edge portion. The second trailing edge portion is disposed aft of the first trailing edge portion. The scarf nozzle is configured to allow the nacelle to be integrated closer to a wing without adversely affecting the pressure gradient between the nacelle and the wing. The scarf nozzle allows a portion of an exhaust plume exiting the aft end of the nacelle to interact more favorably with an airflow along one or more surfaces adjacent the nacelle, thus delaying the onset of adverse pressure gradients and the formation of shock waves between the nacelle and the adjacent surfaces and between the adjacent surfaces and the exhaust plume.

摘要翻译： 用于支撑在机舱内的喷气发动机的围巾喷嘴。 围巾喷嘴位于机舱的后端。 围巾喷嘴包括第一后​​缘部分和第二后缘部分。 第二后缘部分设置在第一后缘部分的后方。 围巾喷嘴构造成允许机舱更靠近机翼集成，而不会不利地影响机舱和机翼之间的压力梯度。 围巾喷嘴允许离开机舱的后端的一部分排气羽流与沿着机舱相邻的一个或多个表面的气流更有利地相互作用，从而延迟不利压力梯度的开始和在机舱之间形成冲击波 和相邻表面之间以及相邻表面和排气羽流之间。

公开(公告)号：US20020190158A1

公开(公告)日：2002-12-19

申请号：US10170381

申请日：2002-06-14

申请人： SNECMA MOTEURS

发明人： Michel Franchet ,  Yann Laugier ,  Jean Loisy

IPC分类号： B64D027/00

CPC分类号： F02K3/04 ,  F02C7/36 ,  F02K3/12 ,  Y02T50/671

摘要： A variable cycle propulsion system for a supersonic airplane comprises at least one engine capable of generating thrust for flight at supersonic speeds together with at least one auxiliary propulsion assembly that is separate from the engine and that is capable of generating additional thrust for takeoff, landing, and flight at subsonic speeds. The auxiliary propulsion assembly does not have a gas generator and means are provided for transmitting a fraction of the mechanical power produced by the engine to the auxiliary propulsion assembly in order to enable it to generate the additional thrust for takeoff, landing, and subsonic cruising flight. Means are provided for decoupling the mechanical transmission means for supersonic cruising flight.

摘要翻译： 用于超音速飞行器的可变循环推进系统包括至少一个能够以超声速度产生飞行的推力的发动机以及与发动机分离的至少一个辅助推进组件，并且能够产生额外的起飞，着陆， 并以亚音速飞行。 辅助推进组件没有气体发生器，并且提供了用于将由发动机产生的机械动力的一部分传递到辅助推进组件的装置，以使其能够产生用于起飞，着陆和亚音速巡航飞行的附加推力 。 提供了用于解耦用于超音速巡航飞行的机械传动装置的装置。

公开(公告)号：US20020084381A1

公开(公告)日：2002-07-04

申请号：US09965942

申请日：2001-09-27

申请人： Lord Corporation

发明人： Jacques Lemire ,  Kirk W. Olsen ,  Francis J. DePriest ,  Thomas R. Law ,  Gerald P. Whiteford ,  Paul J. Bachmeyer

IPC分类号： B64D027/00

CPC分类号： B64D41/00 ,  B64D2041/002

摘要： A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

摘要翻译： 一种用于在飞机尾座中支撑辅助动力单元的系统，其中所述辅助动力单元由支撑所述动力单元的聚焦悬架系统支撑，所述聚焦悬架系统具有多个支撑装置，每个支撑装置具有动作线，所述动作线 在焦点处相交。 支持系统简化了辅助动力单元从飞机尾部的拆卸和安装。

公开(公告)号：US20010032906A1

公开(公告)日：2001-10-25

申请号：US09791442

申请日：2001-02-23

发明人： Thomas R. Weneck ,  Mickey A. Williamson

IPC分类号： B64B001/24 ,  B64D027/00 ,  B64D029/00 ,  B64D031/00 ,  B64D033/00 ,  B64D035/00

CPC分类号： B64F5/10

摘要： An access platform comprising a series of stackable polyurethane foam block assemblies that when properly secured to each other creates a set of steps and handholds similar to a ladder. At the top of the platform a maintenance person can stand on a nonskid surface and perform the work needed at any required height. The ladder is radially curved to fit between the thrust reverser sleeve (deployed) and the inner fan duct wall. This radial diameter between the GE, Rolls Royce and Pratt Whitney engines varies within inches. The main access blocks of the access platform can be used on all three engines by using different foam wedges and wall blocks to secure the assembly tightly in place. Over 70% of the blocks are useable on all three engine types, thus reducing the number of overall parts required. Importantly, a special use tool is provided comprising interlocking foam block modules that are built up in place, are shaped to conform to the engine's inner nacelle wall and are used as a support scaffold for maintenance personnel.

摘要翻译： 一种进入平台，包括一系列可堆叠的聚氨酯泡沫块组件，当彼此适当地固定到彼此时产生类似于梯子的一组步骤和扶手。 在平台的顶部，维护人员可以站在不起眼的表面上，并执行任何所需高度所需的工作。 梯子径向弯曲以配合在推力反向器套筒（展开）和内部风扇管道壁之间。 GE，劳斯莱斯和普拉特惠特尼发动机之间的径向直径在英寸之内变化。 通过使用不同的泡沫楔块和墙体块，可将所有三个发动机的主要通道块用于所有三个发动机，以将组件紧固到位。 所有三种发动机类型都可以使用70％以上的油箱，从而减少了所需的总体零件数量。 重要的是，提供了一种特殊用途工具，其包括互锁的泡沫块模块，其被构建在适当的位置，成形为符合发动机的内部机舱壁并用作维护人员的支撑脚手架。

公开(公告)号：US20040251380A1

公开(公告)日：2004-12-16

申请号：US10839133

申请日：2004-05-06

申请人： SNECMA MOTEURS

发明人： Felix Pasquer ,  Philippe Loewenstein ,  Marc Tesniere

IPC分类号： B64D027/00

CPC分类号： B64D27/26 ,  B64D2027/266 ,  B64D2027/268

摘要： The present invention relates to a suspension of the turbo fan engine to an aircraft pylon, including a fitting (12) arranged to be attached to a pylon, a lever (15) fastened in its central portion (150) to the fitting via a linking means with a pivot pin (150P), and two thrust rods (20, 22) each connected by an end to the lever and including at the other end of the fastening means to the engine. It is characterised in that said linking means is composed on said central portion (150) of the lever, of two parallel branches (151, 152) apart from one another, and on the fitting, of a central fastening tab (133), whereas the fastening tab and both branches are held together by dint of said pivot pin (150P). The invention enables to simplify the manufacture of the parts forming the suspension, thereby improving structural resistance.

摘要翻译： 本发明涉及一种涡轮风扇发动机悬挂在飞机吊架上，该吊架包括布置成连接在塔架上的接头（12），通过连接件固定在其中心部分（150）上的配件 具有枢轴销（150P）的装置和两个推杆（20,22），每个推杆通过端部连接到杠杆并且在紧固装置的另一端处连接到发动机。 其特征在于，所述连接装置在所述杠杆的所述中心部分（150）上由两个彼此分开的平行分支（151,152）和中心紧固片（133）的配件组成，而 所述紧固片和两个分支通过所述枢轴销（150P）的夹持而保持在一起。 本发明能够简化形成悬架的部件的制造，从而提高结构阻力。

公开(公告)号：US20040251379A1

公开(公告)日：2004-12-16

申请号：US10838243

申请日：2004-05-05

申请人： SNECMA MOTEURS

发明人： Felix Pasquer ,  Philippe Loewenstein ,  Marc Tesniere

IPC分类号： B64D027/00

CPC分类号： B64D27/26 ,  B64D2027/266 ,  B64D2027/268

摘要： The present invention relates to a rear attachment suspension or device of a turbo engine (1) to an aircraft pylon including an upper brace (12) fitted with pylon fastening means, whereon are hinged by second ball joint connections (163, 183), three rocker bars transversal to the longitudinal axis of the engine, a first (16) and a second (18) rocker bars on both sides of the axis of the engine and a third rocker bar (17) between both of them, the rocker bars being themselves linked with the engine by first ball joint connections (161, 181). The suspension is characterised in that the first (16) and second (18) rocker bars each include a third (167, 187) stand-by link and in that the upper brace (12) is formed of a beam (120) fixed rigidly to the pylon. The solution of the invention enables the realisation of identical rocker bars and to ensure interchangeability thereof, thereby reducing the risks of error during assembly.

摘要翻译： 本发明涉及一种涡轮发动机（1）的后部附接悬架或装置，该涡轮发动机（1）包括一个装有挂架固定装置的上支架（12），所述上支架（12）由第二球窝接头连接（163,183）铰接， 与发动机的纵向轴线横切的摇杆，在发动机轴线的两侧上的第一（16）和第二（18）摇杆和在它们之间的第三摇杆（17），摇杆是 它们通过第一球窝接头连接（161,181）与发动机连接。 悬架的特征在于，第一（16）和第二（18）摇杆每个包括第三（167,187）备用连杆，并且上支撑件（12）由刚性固定的梁（120）形成 到塔架 本发明的解决方案能够实现相同的摇杆并确保其可互换性，从而减少组装过程中的错误风险。

公开(公告)号：US20040251378A1

公开(公告)日：2004-12-16

申请号：US10379658

申请日：2003-03-06

发明人： Adam M. Bagnall

IPC分类号： B64D027/00

CPC分类号： F02C7/042 ,  B64D33/02 ,  F05D2250/311 ,  F05D2250/411

摘要： An aircraft (10) comprises a wing (12) having an upper surface (16) and a lower surface (18) and at least one turbofan gas turbine engine (20) mounted on the wing (12). The axis (34) of the at least one turbofan gas turbine engine (20) is arranged substantially in the plane (14) of the wing (12) of the aircraft (10). The at least one turbofan gas turbine engine (10) has an intake, the intake comprising a hollow member (44) rotatably mounted coaxially with the at least one turbofan gas turbine engine (20) such that in use the hollow member (44) is rotatable between a first position, a low-speed condition, in which air flowing over and/or above the upper surface (16) of the wing (12) flows into the intake of the at least one turbofan gas turbine engine (20) and a second position, a high-speed condition, in which air flowing along and/or below the lower surface (18) of the wing (12) flows into the intake of the at least one turbofan gas turbine engine (20).

摘要翻译： 飞机（10）包括具有上表面（16）和下表面（18）的翼（12）和安装在翼（12）上的至少一个涡轮风扇燃气涡轮发动机（20）。 至少一个涡轮风扇燃气涡轮发动机（20）的轴线（34）基本上布置在飞行器（10）的机翼（12）的平面（14）中。 所述至少一个涡轮风扇燃气涡轮发动机（10）具有进气口，所述进气口包括与所述至少一个涡轮风扇燃气涡轮发动机（20）同轴地可旋转地安装的中空构件（44），使得在使用中，中空构件（44） 在第一位置和低速状态之间可旋转，在该第一位置和低速状态下，在翼部（12）的上表面（16）上方和/或上方流动的空气流入至少一个涡轮风扇燃气涡轮发动机（20）的进气口，以及 第二位置，高速状态，其中沿翼和（12）的下表面（18）流动的空气流入至少一个涡轮风扇燃气涡轮发动机（20）的进气口。

公开(公告)号：US20040129832A1

公开(公告)日：2004-07-08

申请号：US10475766

申请日：2003-10-22

发明人： Herve Marche

IPC分类号： B64D027/00

CPC分类号： B64D27/26 ,  B64D27/18 ,  B64D2027/264 ,  Y02T50/44

摘要： A strut (10) for hooking an engine (16) under a wing body assembly (12) of an aircraft comprises a rigid structure as well as a mechanism for hooking this structure under the wing body assembly. This mechanism comprises a front fastener (22), a rear fastener (24) and a structure (26) for absorbing thrust. To install an engine (16) of greater diameter under the wing body assembly (12) of an existing plane, the rear part (20b) of the strut (10) is given a width which increases as it progresses to the rear. Furthermore, the rear fastener (24) comprises two braces which are fixed on both sides of the rigid structure and two shackles which connect each of the braces to an additional transverse rib integrated into the wing body assembly.

摘要翻译： 用于将发动机（16）钩在飞行器的翼体组件（12）下方的支柱（10）包括刚性结构以及用于将该结构钩在翼体组件下方的机构。 该机构包括前紧固件（22），后紧固件（24）和用于吸收推力的结构（26）。 为了在现有平面的翼体组件（12）的下方安装更大直径的发动机（16），支柱（10）的后部（20b）的宽度随其向后方的增加而增加。 此外，后紧固件（24）包括固定在刚性结构的两侧上的两个撑杆和将每个支架连接到一体的翼体组件中的另外的横向肋的两个钩环。

公开(公告)号：US20040094664A1

公开(公告)日：2004-05-20

申请号：US10278382

申请日：2002-10-22

发明人： Kenneth M. Harrison ,  Donald T. Powell ,  James R. Schnelz ,  Brett D. Whitmer

IPC分类号： B64D027/00

CPC分类号： B64D27/26 ,  B64D27/18 ,  B64D29/06 ,  Y02T50/44

摘要： Aircraft engine nacelles and methods for structurally attaching them to aircraft structures, such as aircraft wings. In one embodiment, an aircraft engine nacelle is attached to a wing between a trailing edge region of the wing and an aft deck region of the wing. In one aspect of this embodiment, the engine nacelle includes a forward portion having first and second structural attach points offset from each other in a first direction at least generally perpendicular to a central axis of the engine nacelle. The first and second structural attach points can be configured to fixedly attach the engine nacelle to the wing at least proximate to the trailing edge region. In another aspect of this embodiment, the engine nacelle includes a side portion having at least a third structural attach point offset from the first and second structural attach points in a second direction at least generally parallel to the central axis. The third structural attach point can be configured to fixedly attach the engine nacelle to the wing at least proximate to the aft deck region.

摘要翻译： 飞机发动机舱和结构上将其连接到飞机结构（如飞机机翼）上的方法。 在一个实施例中，飞机发动机机舱附接到机翼的后缘区域和机翼的后甲板区域之间的机翼。 在该实施例的一个方面，发动机舱包括前部，其具有第一和第二结构连接点，该第一和第二结构连接点在至少大致垂直于发动机舱的中心轴线的第一方向彼此偏移。 第一和第二结构附接点可被构造成至少靠近后缘区域将发动机舱固定地附接到机翼。 在该实施例的另一方面，发动机舱包括侧部，该侧部具有至少第三结构附着点，该第三结构附着点在至少大致平行于中心轴线的第二方向上偏离第一和第二结构附着点。 第三结构附接点可以构造成将发动机舱固定地附接到机翼，至少靠近后甲板区域。

公开(公告)号：US20030075643A1

公开(公告)日：2003-04-24

申请号：US09938877

申请日：2001-08-24

发明人： James P. Dunn

IPC分类号： B64G001/62 ,  B64D027/00

CPC分类号： B64D27/24 ,  B64D2041/005 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

摘要： Electrically powered aircraft having fuel cells as at least a partial source of electrical energy. In many instances the electrical energy powers an electric motor used to propel the aircraft. In some instances, the electric output from the fuel cell would be augmented by power from special high power nullsurgenull batteries for critical takeoff and climbing, where the maximum electric power is required. In preferred embodiments, such fuel cell powered aircraft will supply oxygen to the fuel cell either from a container of oxygen carried on board the aircraft, or from a ram scoop which directs air through which the aircraft is moving to the fuel cell.

摘要翻译： 电动飞机具有至少部分电能源的燃料电池。 在许多情况下，电能为用于推进飞机的电动机供电。 在某些情况下，来自燃料电池的电力输出将通过来自特殊大功率“浪涌”电池的功率增加，用于需要最大功率的关键起飞和爬升。 在优选实施例中，这种燃料电池供电的飞行器将从飞机上承载的氧气容器或从引导飞机正在移动到燃料电池的空气的冲击勺向燃料电池供应氧气。