公开(公告)号：US07975488B2

公开(公告)日：2011-07-12

申请号：US11495930

申请日：2006-07-28

申请人： Jorge L. Farah ,  William G. Hoop ,  Jose M. Cintron

发明人： Jorge L. Farah ,  William G. Hoop ,  Jose M. Cintron

IPC分类号： F02K1/00

CPC分类号： F02K1/822 ,  F02C7/20 ,  F02K1/004 ,  F02K1/80 ,  Y02T50/671 ,  Y02T50/675

摘要： An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment hanger system. The foldable attachment hanger system provides a low profile (foldable up/down) for a limited access installation envelope typical of a three bearing swivel duct (3BSD) which rotates about three bearing planes to permit transition between a cruise configuration and a hover configuration. In this way, each cooling liner segment may be formed as a complete cylindrical member requiring joints only between the swivelable duct sections.

摘要翻译： 排气管道组件包括与排气管道壳体间隔开的冷却衬套，所述排气管道壳体铰接用于在垂直起落架（STOVL）类型的飞行器中使用。 冷却衬套组件通过可折叠的连接悬挂系统附接到排气管道壳体。 可折叠连接衣架系统为三个轴承旋转管道（3BSD）提供了一个有限的入口安装信封，该三个轴承旋转管道（3BSD）围绕三个轴承平面旋转，以允许在巡航配置和悬停配置之间过渡。 以这种方式，每个冷却衬套段可以形成为仅在可旋转导管段之间仅需要接头的完整圆柱形构件。

公开(公告)号：US20110016879A1

公开(公告)日：2011-01-27

申请号：US11495930

申请日：2006-07-28

申请人： Jorge L. Farah ,  William G. Hoop ,  Jose M. Cintron

发明人： Jorge L. Farah ,  William G. Hoop ,  Jose M. Cintron

IPC分类号： F02C7/20

CPC分类号： F02K1/822 ,  F02C7/20 ,  F02K1/004 ,  F02K1/80 ,  Y02T50/671 ,  Y02T50/675

摘要： An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment hanger system. The foldable attachment hanger system provides a low profile (foldable up/down) for a limited access installation envelope typical of a three bearing swivel duct (3BSD) which rotates about three bearing planes to permit transition between a cruise configuration and a hover configuration. In this way, each cooling liner segment may be formed as a complete cylindrical member requiring joints only between the swivelable duct sections.

摘要翻译： 排气管道组件包括与排气管道壳体间隔开的冷却衬套，所述排气管道壳体铰接用于在垂直起落架（STOVL）类型的飞行器中使用。 冷却衬套组件通过可折叠的连接悬挂系统附接到排气管道壳体。 可折叠连接衣架系统为三个轴承旋转管道（3BSD）提供了一个有限的入口安装信封，该三个轴承旋转管道（3BSD）围绕三个轴承平面旋转，以允许在巡航配置和悬停配置之间过渡。 以这种方式，每个冷却衬套段可以形成为仅在可旋转导管段之间仅需要接头的完整圆柱形构件。

公开(公告)号：US20080169375A1

公开(公告)日：2008-07-17

申请号：US11864272

申请日：2007-09-28

申请人： Rikiya ISHIKAWA

发明人： Rikiya ISHIKAWA

IPC分类号： B64C29/00 ,  B64D27/10

CPC分类号： F02K9/78 ,  B64C29/0025 ,  F02C3/107 ,  F02K1/004 ,  F05D2220/90

摘要： The flying body includes a body (100a), a lift engine (102a1), and reaction control engines. The lift engine includes, a gas generator (200a1) for generating a turbine driving gas, a first thrust device (204a1, 208a1, 210a1) for providing a power by the turbine driving gas and exhausting a gas (20a1) in a predetermined direction to generate a first thrust force, a second thrust device (214a1, 218a1, 220a1) driven by the power to suck and compress a surrounding gas (21a1) and to accelerate and exhaust the surrounding gas substantially in a direction of a flow of the gas exhausted by the first thrust device to generate a second thrust force to be added to the first thrust force. The gas generator generates a gas by using a raw material (10, 11a) for gas generation carried by the flying body. The first thrust device has a turbine (204a1, 208a1) for obtaining a rotational force, and the second thrust device has a fan (214a1, 218a1) driven by the rotational force obtained by the turbine, and a nozzle (222a1) in a downstream of the fan.

摘要翻译： 飞行体包括主体（100a），升降机引擎（102a）和反应控制引擎。 提升发动机包括用于产生涡轮驱动气体的气体发生器（200a 1），用于通过涡轮驱动气体提供动力并排出气体的第一推力装置（204a，208a，210a1） （20a），以产生第一推力;第二推力装置（214a，218a，1,2a，a1a），其被所述动力驱动以吸收和压缩周围的气体（21a）和 基本上沿着由第一推力装置排出的气体的流动的方向加速和排出周围的气体，以产生要加到第一推力的第二推力。 气体发生器通过使用用于由飞行体携带的气体产生的原料（10,11a）产生气体。 第一推力装置具有用于获得旋转力的涡轮机（204a，208a1），并且第二推力装置具有由涡轮机获得的旋转力驱动的风扇（214a，218a1），以及 在所述风扇的下游的喷嘴（222a1）。

公开(公告)号：US20050155352A1

公开(公告)日：2005-07-21

申请号：US11010454

申请日：2004-12-14

申请人： Michael Agg

发明人： Michael Agg

IPC分类号： F02K1/00 ,  F02K1/04 ,  F16L7/00 ,  F16L9/18 ,  F16L39/04 ,  F16L57/02

CPC分类号： F16L7/00 ,  F02K1/004 ,  F16L9/18 ,  F16L9/20 ,  F16L39/04 ,  F16L57/02 ,  Y10T403/7005

摘要： A duct comprising an inner casing spaced apart from an outer casing and which also comprises a number of interfaced duct sections must be assembled in such a way to prevent relative redial movement between the casings and thereby inhibit buckling. The present invention is a duct which utilises abutment members which longitudinally extend from each of the inner walls across the interface of the duct sections. The abutment members are radially spaced apart in normal use but are configured such that substantially relative radial movement of the inner and outer walls is prevented when the overlapping members abut.

摘要翻译： 包括与外壳间隔开并且还包括多个接口管道部分的内壳的管道必须以这样的方式组装以防止壳体之间的相对重拨运动，从而抑制弯曲。 本发明是一种管道，其利用从每个内壁纵向延伸穿过管道段的界面的邻接构件。 邻接构件在正常使用中径向间隔开，但是构造成使得当重叠构件抵接时，防止内壁和外壁的基本上相对的径向移动。

公开(公告)号：US06918244B2

公开(公告)日：2005-07-19

申请号：US10216395

申请日：2002-08-12

申请人： John Eugene Dickau

发明人： John Eugene Dickau

IPC分类号： B64C15/02 ,  B64C29/00 ,  F02K1/00 ,  F02K1/64 ,  F02K1/66 ,  F02K1/72 ,  F02K3/02 ,  F02K3/075

CPC分类号： B64C29/0066 ,  B64C15/02 ,  F02K1/004 ,  F02K1/64 ,  F02K1/66 ,  F02K1/72 ,  F02K3/02 ,  F02K3/025 ,  F02K3/075 ,  F05D2220/90 ,  Y02T50/672

摘要： This patent concerns VTOL propulsion systems that develop a forward flow of air through the air intake duct(s), by the methods of a internal duct system, reversing the rotation of the fan, or a variable pitch (thrust reversing) fan.

摘要翻译： 该专利涉及通过内部管道系统的方法，反转风扇的旋转或可变节距（推力反向）风扇来开发空气通过进气管道的前向流动的垂直起降推进系统。

公开(公告)号：US20050120702A1

公开(公告)日：2005-06-09

申请号：US10731368

申请日：2003-12-09

申请人： Lawrence Fink

发明人： Lawrence Fink

IPC分类号： F02K1/00

CPC分类号： F02K1/004 ,  F02K1/002 ,  F05D2250/42

摘要： A nozzle for a jet engine generally includes a nozzle rim and a bendable duct for communicating an exhaust flow generated by the engine to the nozzle rim. A gimbal joint pivotably couples the nozzle rim to supporting structure. The gimbal joint allows the nozzle rim to be pivoted about a first axis and a second axis, thereby allowing changes to the vector at which the exhaust flow is discharged from the nozzle rim.

摘要翻译： 用于喷气发动机的喷嘴通常包括喷嘴边缘和用于将由发动机产生的排气流连通到喷嘴边缘的可弯曲管道。 万向接头将喷嘴边缘可枢转地联接到支撑结构。 万向接头允许喷嘴边缘围绕第一轴线和第二轴线枢转，从而允许改变从喷嘴边缘排出废气流的向量。

公开(公告)号：US20040017045A1

公开(公告)日：2004-01-29

申请号：US10368640

申请日：2003-02-20

申请人： CROSS MANUFACTURING COMPANY (1938) LIMITED

发明人： Rodney Alan Cross ,  Paul Anthony Blanchard

IPC分类号： F16J015/34

CPC分类号： F02K1/805 ,  F02K1/004 ,  F02K1/80 ,  F16J15/0887 ,  F16J15/3452 ,  F16J15/348 ,  F16L25/0018 ,  F16L27/082 ,  Y02T50/671

摘要： A jet pipe assembly containing at least one joint provided with a seal assembly to isolate, substantially, the fluid flowing in the pipe from the fluid external to the pipe. The dynamic member of the seal assembly is provided with both radial and cylindrical sealing surfaces.

摘要翻译： 一种喷射管组件，其包含至少一个具有密封组件的接头，该密封组件基本上将管道中流动的流体与管外部的流体隔离开。 密封组件的动态构件设置有径向和圆柱形密封表面。

公开(公告)号：US6109663A

公开(公告)日：2000-08-29

申请号：US179425

申请日：1998-10-27

申请人： Paul R Hayton

发明人： Paul R Hayton

IPC分类号： F02K1/00 ,  F02K1/80 ,  F16L27/08 ,  F16L27/00

CPC分类号： F16L27/0828 ,  F02K1/004 ,  F02K1/805

摘要： A joint seal for articulated joints between contra-rotating sections of a gas turbine engine exhaust duct. The illustrated embodiment comprises a plurality of contra-rotatable exhaust duct sections leading to a vectorable final nozzle. The joint seal is located internally of a bearing around its inner circumference. An exhaust section may have an internal wall spaced internally from the outer wall, thus forming an annular space for conducting relatively cool air surrounding the hot gas stream. The joint seals preferably are located between adjacent ends of these inner walls.

摘要翻译： 用于燃气涡轮发动机排气管的反转部分之间的铰接接头的接头密封。 所示实施例包括通向可向量的最终喷嘴的多个可反转的排气管段。 接头密封件位于围绕其内圆周的轴承的内部。 排气部分可以具有与外壁间隔开的内壁，从而形成环形空间，用于传导围绕热气流的相对较冷的空气。 接头密封件优选地位于这些内壁的相邻端部之间。

公开(公告)号：US5996935A

公开(公告)日：1999-12-07

申请号：US871880

申请日：1997-06-02

申请人： Leonard Stanley Snell

发明人： Leonard Stanley Snell

IPC分类号： B64C3/50 ,  B64C29/00 ,  F02K1/00 ,  F02K3/02

CPC分类号： B64C3/50 ,  B64C29/0066 ,  F02K1/004 ,  F02K3/025 ,  Y02T50/671

摘要： An aircraft power plant for vertical take-off and landing comprises a jet propulsion unit having an air inlet and an exhaust outlet and incorporating a combustion chamber, a high pressure compressor for supplying air from the air inlet to the combustion chamber, a fuel inlet for supplying fuel to the combustion chamber, and a turbine coupled to drive the compressor and arranged to be driven by the exhaust gases passing from the combustion chamber to the exhaust outlet. Swivelling front nozzles are provided for selectively directing a proportion of air from a fan arrangement downwardly in front of the propulsion unit and swivelling rear nozzles are provided for selectively directing at least a proportion of the exhaust gases from the exhaust outlet downwardly to the rear of the propulsion unit, in order to effect lift on take-off or landing. The fan arrangement comprises a first fan for supplying air to the front nozzles and a second fan, positioned rearwardly of the first fan, for supplying air to the air inlet of the propulsion unit, as well as a shaft having a length which is chosen to position the front nozzles sufficiently far forward to produce the required moment about the aircraft centre of gravity. Such an arrangement provides a highly efficient power plant which can be accommodated within a narrow cross-section, and which can be implemented without requiring gearboxes, clutches or hot ducts.

摘要翻译： 用于垂直起飞和着陆的飞机发电厂包括具有空气入口和排气出口并结合有燃烧室的喷射推进单元，用于从空气入口向燃烧室供应空气的高压压缩机，用于 向燃烧室供应燃料，以及涡轮机，其联接以驱动压缩机并被布置成被从燃烧室通过排气出口的废气驱动。 提供旋转前喷嘴用于选择性地将来自风扇装置的一部分空气从推进单元的前方向下引导，并且提供旋转后喷嘴用于选择性地将至少一部分排气从排气出口向下排列到 推进单元，以便起飞或降落时起升力作用。 风扇装置包括用于向前喷嘴供应空气的第一风扇和位于第一风扇后方的用于向推进单元的空气入口供应空气的第二风扇，以及具有选择为 将前喷嘴定位得足够远，以产生关于飞机重心的所需时刻。 这种布置提供了可以容纳在窄横截面内并且可以在不需要变速箱，离合器或热管的情况下实现的高效率发电厂。

公开(公告)号：US5769317A

公开(公告)日：1998-06-23

申请号：US433675

申请日：1995-05-04

申请人： Jack (Jagdish) Singh Sokhey ,  Andrew James Crook ,  Philip Harold Snyder ,  Baily R. Vittal

发明人： Jack (Jagdish) Singh Sokhey ,  Andrew James Crook ,  Philip Harold Snyder ,  Baily R. Vittal

IPC分类号： B64C15/02 ,  B64C29/00 ,  F02K1/00 ,  F02K3/02 ,  F02K1/78

CPC分类号： F02K1/002 ,  B64C15/02 ,  B64C29/0058 ,  F02K1/004 ,  F02K1/008 ,  F02K3/025

摘要： A thrust vectoring system comprising a working fluid source mounted to an aircraft, and a vectoring nozzle connected to the working fluid source which has an extendable conduit defining a passage from an inlet to an outlet. The passage is adjustable so that the direction of the working fluid exiting the outlet is different than the working fluid entering the inlet when the conduit of the vectoring nozzle is extended. This conduit provides a way to change the direction of working fluid exiting the nozzle and correspondingly change the thrust vector of the aircraft. A directing member such as a guide vane or door is mounted to the conduit adjacent the outlet to further direct the working fluid exiting the outlet. Directing members provide a way to refine the thrust vector without changing the extension of the segmented conduit. Another aspect of the present invention is to provide an adapter to connect the vectoring nozzle to a working fluid source with an annular outlet. This adapter uses an asymmetric structure to minimize flow separation.

摘要翻译： 包括安装到飞行器的工作流体源的推力矢量系统和连接到工作流体源的矢量喷嘴，其具有限定从入口到出口的通道的可延伸导管。 该通道是可调节的，使得离开出口的工作流体的方向不同于当向量化喷嘴的管道延伸时进入入口的工作流体。 该管道提供了改变离开喷嘴的工作流体的方向并相应地改变飞机的推力矢量的方式。 诸如导向叶片或门的引导构件安装到靠近出口的导管，以进一步引导离开出口的工作流体。 引导构件提供了一种改进推力矢量的方法，而不改变分段导管的延伸。 本发明的另一方面是提供一种用于将引导喷嘴连接到具有环形出口的工作流体源的适配器。 该适配器使用非对称结构来最小化流分离。