公开(公告)号：US08256203B1

公开(公告)日：2012-09-04

申请号：US12021142

申请日：2008-01-28

申请人： James B. Blackmon ,  David B. Landrum ,  Sean Entrekin

发明人： James B. Blackmon ,  David B. Landrum ,  Sean Entrekin

IPC分类号： F02K3/00

CPC分类号： F02K9/52 ,  F02K1/004 ,  F02K3/025 ,  F02K7/16 ,  F02K7/18 ,  F02K9/78

摘要： The present disclosure generally pertains to rocket based combined cycle (RBCC) propulsion units. In one exemplary embodiment, at least one rocket thruster is integrated with a jet engine but is external to the flow path of the jet engine, forming an altitude compensating plug nozzle. Since the rocket thruster is external to such flow path, the rocket flow from the rocket thruster interacts with the jet flow from the jet engine aft of the nozzle of the jet engine. Such interaction occurs without a significant performance penalty in the operation of the jet engine. In fact, it is possible that the interaction of the rocket flow with the jet flow may actually improve the efficiency of the jet engine under some conditions. Moreover, having the rocket thrusters positioned external to the flow path of the jet engine helps to avoid many of the problems plaguing conventional RBCC propulsion units.

摘要翻译： 本公开通常涉及基于火箭的联合循环（RBCC）推进单元。 在一个示例性实施例中，至少一个火箭推进器与喷气发动机集成在一起，但是在喷气发动机的流动路径的外部，形成高度补偿塞子喷嘴。 由于火箭推进器在这种流动路径的外部，所以来自火箭推进器的火箭流与来自喷气发动机的喷嘴后部的喷气发动机的喷射流相互作用。 这种相互作用在喷气发动机的操作中没有显着的性能损失。 事实上，火箭流与射流的相互作用有可能在某些条件下实际上提高喷气发动机的效率。 此外，将火箭推进器定位在喷气发动机的流动路径的外部有助于避免困扰常规RBCC推进装置的许多问题。

公开(公告)号：US20110016880A1

公开(公告)日：2011-01-27

申请号：US12510216

申请日：2009-07-27

申请人： Steven D. Roberts ,  Jocelyn Charis Damgaard

发明人： Steven D. Roberts ,  Jocelyn Charis Damgaard

IPC分类号： F02C7/20 ,  F02K1/80

CPC分类号： F02K1/80 ,  F02C7/20 ,  F02K1/004 ,  F02K1/06 ,  F05B2260/301 ,  F05D2250/141

摘要： A hanger system includes a pin with a head section which defines a pin axis. A clip assembly captures the head section to permit movement of the pin within a hanger in a direction traverse to the pin axis. A fastener which retains the clip assembly to the hanger.

摘要翻译： 衣架系统包括具有限定销轴的头部的销。 夹子组件捕获头部部分，以允许销在移动到销轴的方向上的悬挂器内移动。 将夹子组件保持在衣架上的紧固件。

公开(公告)号：US20100301158A1

公开(公告)日：2010-12-02

申请号：US12761155

申请日：2010-04-15

申请人： Paul J.H. HARRIS ,  Frank A. Hewitt ,  Martin C. Johnson ,  Christopher Wright

发明人： Paul J.H. HARRIS ,  Frank A. Hewitt ,  Martin C. Johnson ,  Christopher Wright

IPC分类号： B64C29/00

CPC分类号： B64C29/0016 ,  B64C15/14 ,  B64C29/0075 ,  B64D2027/026 ,  F02C3/10 ,  F02K1/004 ,  F02K5/00 ,  F05D2220/328 ,  F05D2220/76 ,  Y02T50/671

摘要： An aircraft having a lift/propulsion unit which includes a power unit such as a turboshaft engine which drives a fan through a transmission mechanism. The fan discharges to vectoring nozzles which can be independently swivelled to provide lift or propulsion thrust. An output shaft of the transmission mechanism serves as the main shaft of a motor/generator of modular form. The motor/generator can act as a generator to charge an electrical storage device such as a battery, or as a motor to drive the fan, either alone or to supplement the output of engine. Reaction control nozzles are provided at extremities of the aircraft to provide stabilising thrust. The aircraft is capable of vertical take off and hovering, with the vectoring nozzles swivelled to a lift position, and forward thrust with the vectoring nozzles swivelled to a propulsion position.

摘要翻译： 一种具有提升/推进单元的飞机，其包括诸如通过传动机构驱动风扇的涡轮轴发动机的动力单元。 风扇排放到可独立旋转的向导喷嘴，以提供升力或推进推力。 传动机构的输出轴用作模块式电机/发电机的主轴。 电动机/发电机可以用作发电机，以对诸如电池的电存储装置或作为驱动风扇的电动机单独充电或补充发动机的输出。 反应控制喷嘴设置在飞行器的末端以提供稳定的推力。 该飞机能够垂直起飞和悬停，矢量喷嘴旋转到提升位置，并向前推动矢量喷嘴旋转到推进位置。

公开(公告)号：US20090230213A1

公开(公告)日：2009-09-17

申请号：US12046411

申请日：2008-03-11

申请人： Andrew H. Harris

发明人： Andrew H. Harris

IPC分类号： B05B12/00

CPC分类号： F02K1/822 ,  B22F3/225 ,  B22F5/00 ,  B22F5/009 ,  C04B35/638 ,  F02K1/004 ,  F02K1/78 ,  F02K1/82 ,  F05D2230/21 ,  Y02T50/675

摘要： An exhaust duct assembly includes an attachment hanger system having at least one component manufactured by metal injection molding (MIM).

摘要翻译： 排气管道组件包括具有通过金属注射成型（MIM）制造的至少一个部件的附接衣架系统。

公开(公告)号：US20070081754A1

公开(公告)日：2007-04-12

申请号：US11521498

申请日：2006-09-15

申请人： Michael Roberts

发明人： Michael Roberts

IPC分类号： F16C33/00

CPC分类号： F02K1/004 ,  F16C19/163

摘要： The present invention provides an actuating apparatus for moving relatively rotatable components. In one embodiment the apparatus comprises: a bearing (30) including first (34) and second (36) relatively rotatable bearing elements for mounting respective first (18) and second (12) rotatable components for relative rotation about a common axis; a pneumatic or hydraulic actuator having a pair of co-acting parts (44, 54), including a first part (54) fixed with respect to the said first rotatable element and a second part (44) fixed with respect to the said second rotatable element; and, means (110) for energising and/or de-energising said actuator means to effect movement of the said co-acting parts and thereby relative rotation of the said first and second bearing elements about the said bearing axis. The actuator may comprise at least one chamber (52) defined between a pair of relatively rotatable annular members (44, 54) each having at least one dividing element (66, 68, 70) extending into the chamber to divide the interior of the chamber into separate circumferential regions (80, 82, 84). Pressure differentials generated in the chamber across one or more of the dividing elements effect relative rotation of the first and second bearing elements.

摘要翻译： 本发明提供一种用于移动相对可旋转部件的致动装置。 在一个实施例中，装置包括：轴承（30），包括第一（34）和第二（36）相对可旋转的轴承元件，用于安装相应的第一（18）和第二（12）可旋转部件，用于围绕公共轴线相对旋转; 具有一对共同作用部分（44,54）的气动或液压致动器，包括相对于所述第一可旋转元件固定的第一部分（54）和相对于所述第二可旋转元件固定的第二部分（44） 元件; 以及用于激励和/或断开所述致动器装置的装置（110），以实现所述协同作用部件的运动，从而使所述第一和第二轴承元件围绕所述轴承轴线相对旋转。 致动器可以包括限定在一对相对可旋转的环形构件（44,54）之间的至少一个腔室（52），每个腔室具有延伸到腔室中的至少一个分隔元件（66,68,70），以分隔腔室的内部 分成圆周区域（80,82,84）。 通过一个或多个分隔元件在室中产生的压力差影响第一和第二轴承元件的相对旋转。

公开(公告)号：US20030154707A1

公开(公告)日：2003-08-21

申请号：US09949492

申请日：2001-09-07

发明人： Bobby W. Sanders ,  Lois J. Weir

IPC分类号： F02K005/02

CPC分类号： F02K7/02 ,  F02C7/04 ,  F02K1/004 ,  F02K5/02 ,  F02K7/10 ,  Y02T50/671 ,  Y10T137/0536

摘要： A rotary inlet flow controller, with one or more open ducts extending therethrough, aerodynamically controls the amount and velocity of the flow of air to combustion chambers of pulse detonation engines, or other engines, without imposing large cyclic airflow transients in the diffuser of the air intake. The ducted rotary inlet flow controller supplies airflow and sealing in synchronization with the cycles of the engine: airflow and fueling supply, sealing, combustion, and re-opening for additional airflow. This controller will supply near-uniform, continuous airflow to the engine. The preferred controller has one or more propeller-like blades that are designed to cyclically and sequentially duct incoming flow to the inlet ports of the combustion chambers, while also providing the capability of sealing the ports during combustion. The blades are aerodynamically designed to provide the desired converging airflow ducting area between the blades from the entrance to the exit to effect proper matching of the airflow from any air intake to a pulse detonation engine.

摘要翻译： 旋转入口流量控制器具有延伸穿过其中的一个或多个开放管道，空气动力地控制空气流到脉冲爆震发动机或其他发动机的燃烧室的量和速度，而不会在空气扩散器中施加大的循环气流瞬变 摄入量 导管旋转进气流量控制器与发动机循环同步地提供气流和密封：气流和加油供应，密封，燃烧和重新打开以增加气流。 该控制器将为发动机提供近乎均匀的连续气流。 优选的控制器具有一个或多个螺旋桨状叶片，其被设计成循环地并且顺序地将进入的流引导到燃烧室的入口端口，同时还提供在燃烧期间密封端口的能力。 叶片是空气动力学设计的，以在从入口到出口的叶片之间提供期望的会聚气流管道区域，以实现气流从任何进气口到脉冲爆震发动机的适当匹配。

公开(公告)号：US5797544A

公开(公告)日：1998-08-25

申请号：US721889

申请日：1996-09-27

申请人： Eric J. Ward

发明人： Eric J. Ward

IPC分类号： F02K1/00 ,  F02K1/12 ,  F02K1/15 ,  B64C15/08

CPC分类号： F02K1/004 ,  F02K1/1223 ,  F02K1/15 ,  F05D2260/15 ,  Y02T50/671

摘要： The flaps of the C/D exhaust nozzle for a gas turbine engine are arranged to obtain synchronous movement relative to each other and the interconnecting fulcrum links are attached to a coaxially mounted combined piston/sync ring by an H-shaped link. One link from one convergent flap is connected to one of the fulcrum links and the adjacent convergent flap is connected to the same fulcrum link. The redundant synchronization provided by the H-shaped links and flap connections provide damping of the flap train. The fulcrum links are judiciously mounted between adjacent convergent flaps.

摘要翻译： 用于燃气涡轮发动机的C / D排气喷嘴的翼片被布置成获得相对于彼此的同步运动，并且互连支点链节通过H形连杆附接到同轴安装的组合活塞/同步环。 来自一个会聚舌片的一个连接件连接到一个支点连杆，并且相邻的会聚舌片连接到相同的支点连杆。 由H形连杆和襟翼连接提供的冗余同步提供了挡板系统的阻尼。 支点链接明智地安装在相邻的收缩瓣之间。

公开(公告)号：US5794850A

公开(公告)日：1998-08-18

申请号：US721888

申请日：1996-09-27

申请人： Jose L. Gutierrez, Jr.

发明人： Jose L. Gutierrez, Jr.

IPC分类号： F02K1/00 ,  F02K1/12 ,  F02K1/15 ,  F02K1/78 ,  B64C15/06

CPC分类号： F02K1/1223 ,  F02K1/004 ,  F02K1/15 ,  F05D2260/15 ,  Y02T50/677

摘要： The C/D axisymmetrical exhaust nozzle for a gas turbine engine is designed to fit on the engine and STOVL aircraft and includes an hydraulic actuator and a combined load balancing piston/sync ring that is judiciously mounted in the assembly and discretely attached to a fulcrum link and the mechanism is enclosed between concentrically spaced static structure for defining a full-hoop configuration. The actuator is attached to flanges formed on the static structure to allow for access to the attaching bolts. Rollers are mounted on the sync ring to ease the rectilinear movement of the sync ring. Positioning the actuator rectilinearly rotates the fulcrum and connecting links to position the flaps for varying the throat size and C/D configuration for optimum engine performance.

摘要翻译： 用于燃气涡轮发动机的C / D轴对称排气喷嘴被设计成装配在发动机和STOVL飞机上，并且包括液压致动器和组合的负载平衡活塞/同步环，其被明智地安装在组件中并且离散地附接到支点连杆 并且该机构被封闭在同心间隔的静态结构之间以用于限定全环构型。 致动器附接到形成在静态结构上的凸缘，以允许接近安装螺栓。 滚轮安装在同步环上，以缓解同步环的直线运动。 定位执行机构直线地旋转支点和连接链路以定位襟翼，以改变喉咙尺寸和C / D配置，以获得最佳的发动机性能。

公开(公告)号：US4519543A

公开(公告)日：1985-05-28

申请号：US376388

申请日：1982-04-07

申请人： Gary F. Szuminski ,  Thomas J. Jones

发明人： Gary F. Szuminski ,  Thomas J. Jones

IPC分类号： F02K1/00 ,  B63H11/10

CPC分类号： F02K1/004 ,  Y02T50/671

摘要： A vectorable nozzle 17 comprising a fixed first duct 21 a rotatable second duct 22 scarfed at its rear end and a rotatable third duct 23 scarfed at its front end. The second and third ducts 22,23 are mounted in bearings 24,26 respectively and the bearing 26 is constrained to swing bodily about trunnions 29, the axis of which lies transverse to the ducts 22,23, and a screw jack 32 is provided to rotate the bearing 26 about the trunnions 29. The second and third ducts 22,23 are provided with means to rotate them in opposite directions in syncronism with the rotation of the bearing 26 in the trunnion 29.

摘要翻译： 可向引导的喷嘴17包括固定的第一管道21，在其后端处被切割的可旋转的第二管道22和在其前端被切割的可旋转的第三管道23。 第二和第三管道22,23分别安装在轴承24,26中，轴承26被约束以围绕耳轴29摆动，轴颈29的轴线横向于管道22,23，并且螺钉千斤顶32被设置成 使轴承26围绕耳轴29旋转。第二和第三导管22,23设置有与轴承26在耳轴29中的旋转同步的相反方向旋转它们的装置。

公开(公告)号：US3525475A

公开(公告)日：1970-08-25

申请号：US3525475D

申请日：1968-11-06

申请人： MOTOREN TURBINEN UNION

发明人： SCHWEIKL LUDWIG

IPC分类号： B64C9/38 ,  B64C15/04 ,  F02K1/24 ,  F16H1/20

CPC分类号： F02K1/004 ,  B64C9/38 ,  F05D2260/53 ,  Y10T74/19679