公开(公告)号：US06318071B2

公开(公告)日：2001-11-20

申请号：US09066331

申请日：1998-07-07

申请人： Jan Häggander ,  Lars-Olof Pekkari

发明人： Jan Häggander ,  Lars-Olof Pekkari

IPC分类号： F02K100

CPC分类号： F02K9/97 ,  F05D2250/713

摘要： A rocket nozzle having an axial double bell shape. The nozzle includes a first bell shape, a second bell shape and an inflection point where the first bell shape and the second bell shape meet. The inflection point is located between a location at the area ratio &egr;=10 and a location at 0.85×&egr;max of the nozzle, where &egr; is the narrowest cross-sectional area of the nozzle. The first bell shape and the second bell shape both have a contour line having an outwardly directed curvature of between 2 and 7 at the inflection point.

摘要翻译： 具有轴向双钟形状的火箭喷嘴。 喷嘴包括第一钟形状，第二钟形状和第一钟形状和第二钟形形状相交的拐点。 拐点位于喷嘴的面积比εi= 10的位置和0.85xepsimax的位置之间，其中epsi是喷嘴的最窄横截面面积。 第一钟形和第二钟形都具有在拐点处具有2至7之间的向外曲率的轮廓线。

公开(公告)号：US06298658B1

公开(公告)日：2001-10-09

申请号：US09451898

申请日：1999-12-01

申请人： Michael J. Bak

发明人： Michael J. Bak

IPC分类号： F02K100

CPC分类号： F02K9/82 ,  F02K1/28 ,  F05D2240/128 ,  F05D2250/311 ,  F05D2250/313 ,  F05D2250/314

摘要： A stream of primary gas flowing through a bi-stable thrust vectoring nozzle becomes attached to a first or second surface extending downstream of the nozzle, each surface incorporating one or more control ports for controlling to which surface the stream is attached, wherein relative to the longitudinal axis of the nozzle, the angle of discharge from the first surface is substantially different from the angle of discharge from the second surface, preferably with the first surface substantially aligned with the longitudinal axis of the nozzle. In one embodiment, a plurality of nozzles are arranged with the respective first surfaces substantially aligned with the longitudinal axis of the nozzle combination and each of the respective second surfaces arranged to laterally deflect a respective portion of the stream of primary gas in a respective direction along each of two orthogonal lateral axes.

摘要翻译： 流过双稳定推力向量喷嘴的初级气体流附接到延伸到喷嘴下游的第一或第二表面，每个表面包括一个或多个控制端口，用于控制流连接到该表面，其中相对于 喷嘴的纵向轴线，来自第一表面的排出角度与从第二表面排出的角度大致不同，优选地，第一表面基本上与喷嘴的纵向轴线对准。 在一个实施例中，多个喷嘴被布置成具有相应的第一表面基本上与喷嘴组合的纵向轴线对准，并且各个相应的第二表面中的每一个布置成沿着相应的方向沿着主要气体流的相应部分横向偏转 两个正交横轴各有一个。

公开(公告)号：US06260800B1

公开(公告)日：2001-07-17

申请号：US09399178

申请日：1999-09-20

申请人： Leonard Stanley Snell

发明人： Leonard Stanley Snell

IPC分类号： F02K100

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 center 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：US06173807B1

公开(公告)日：2001-01-16

申请号：US09059797

申请日：1998-04-13

申请人： John M. Welch ,  Thomas D. Popp ,  Robert F. Wikstrom ,  Terry W. Stratton ,  Brian R. Kitt

发明人： John M. Welch ,  Thomas D. Popp ,  Robert F. Wikstrom ,  Terry W. Stratton ,  Brian R. Kitt

IPC分类号： F02K100

CPC分类号： G10K11/172 ,  G10K11/161 ,  Y10T29/49398

摘要： An acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a honeycomb-core material (74) sandwiched therebetween. The acoustic panel (26) includes an integral forward ring (36) and integral wedge fairings (44).

摘要翻译： 用于高旁路喷气发动机的机舱（20）的声学板（26）。 声学板（26）具有穿孔复合内片（54），外复合片（96,98）和夹在其间的蜂窝芯材（74）。 声学面板（26）包括整体式前环（36）和整体楔形整流罩（44）。

公开(公告)号：US06745570B2

公开(公告)日：2004-06-08

申请号：US10061618

申请日：2002-02-01

申请人： Bernard J. Renggli ,  Darrell Senile

发明人： Bernard J. Renggli ,  Darrell Senile

IPC分类号： F02K100

CPC分类号： F02K1/12 ,  F05D2230/60 ,  Y10S29/904 ,  Y10T29/49346 ,  Y10T29/494

摘要： A method for assembling a flap system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates extending a useful life of the exhaust nozzle. The method includes providing a flap basesheet having a width defined between a pair of side edges that are coupled together by a leading edge and a trailing edge, and including at least one stiffener that extends between the basesheet side edges and includes an intermediate portion that has a width that is smaller than that of the basesheet and is at least one of bonded to and formed integrally with the basesheet, and coupling the basesheet to the gas turbine engine with a backbone assembly.

摘要翻译： 一种用于组装用于包括多个主干组件的燃气涡轮发动机排气喷嘴的翼片系统的方法有助于延长排气喷嘴的使用寿命。 该方法包括提供一个翼片基片，其宽度限定在一对侧边缘之间，该对侧边缘通过前缘和后缘连接在一起，并且包括至少一个在基片侧边缘之间延伸的加强件，并包括中间部分， 其宽度小于基片的宽度，并且是与基片结合并与基片一体形成的至少一个，并且将基片与骨架组件连接到燃气涡轮发动机。

公开(公告)号：US06412283B1

公开(公告)日：2002-07-02

申请号：US09668451

申请日：2000-09-22

申请人： Yogendra Sheoran ,  Knauer E. Chad ,  Bert A. Diehl, Jr. ,  Timothy R. Whittemore

发明人： Yogendra Sheoran ,  Knauer E. Chad ,  Bert A. Diehl, Jr. ,  Timothy R. Whittemore

IPC分类号： F02K100

CPC分类号： F02K1/386 ,  F02K1/48 ,  F05D2260/96

摘要： A tailpipe for a gas turbine engine has a cylindrical portion and lobed portion. The lobed portion extends a length X and has a plurality of circumferentially disposed peaks and valleys. Over at least the first 30 percent of length X, the radius of the each valley is greater than the radius of each peak and is greater than 10% of the equivalent diameter DE. Also, the effective flow area at the end of the lobed portion is greater that the effective flow area at its beginning. The cylindrical portion includes a straight portion and a canted portion.

摘要翻译： 用于燃气涡轮发动机的尾管具有圆柱形部分和叶形部分。 叶部延伸长度X并且具有多个周向设置的峰和谷。 至少长度X的前30％，每个谷的半径大于每个峰的半径，并且大于等效直径DE的10％。 此外，叶部末端的有效流动面积大于开始时的有效流动面积。 圆柱形部分包括直的部分和倾斜部分。

公开(公告)号：US06349539B1

公开(公告)日：2002-02-26

申请号：US09613733

申请日：2000-07-11

申请人： Didier Georges Feder ,  Daniel Kettler ,  Guy Jean-Louis Lapergue ,  Bertrand Pierre Renaud Monville ,  Jacky Serge Naudet ,  Laurent Claude Patrick Salperwyck

发明人： Didier Georges Feder ,  Daniel Kettler ,  Guy Jean-Louis Lapergue ,  Bertrand Pierre Renaud Monville ,  Jacky Serge Naudet ,  Laurent Claude Patrick Salperwyck

IPC分类号： F02K100

CPC分类号： F02K1/1223 ,  F02K1/008 ,  F02K1/15 ,  F05D2250/323 ,  F05D2250/324 ,  F05D2250/33

摘要： An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring (13). The vectoring ring (13) is driven by linear actuators (20) anchored in the stationary structure (2). The linear actuators (20) are connected by a swivel (22) to the vectoring ring (13) and are affixed to the stationary structure (2) to absorb the tangential loads applied by the exhaust gases on the diverging flaps and to allow positioning the vectoring ring (13). Preferably the linear actuator (20) is connected by a sheath (25) to the vectoring ring (13), the sheath (25) slidable on the actuator case (26) and being displaceable in a radial plane passing through the turbojet-engine's axis.

摘要翻译： 用于喷射偏转的轴对称，会聚 - 分流涡轮喷气发动机排气喷嘴。 发条襟翼通过链接方式连接到矢量环（13）。 矢量环（13）由锚定在固定结构（2）中的线性致动器（20）驱动。 线性致动器（20）通过旋转件（22）连接到引导环（13）并且固定到固定结构（2）以吸收由排气施加在发散翼上的切向负载，并且允许 矢量环（13）。 优选地，线性致动器（20）通过护套（25）连接到引导环（13），护套（25）可在致动器壳体（26）上滑动并且可在穿过涡轮喷气发动机的轴线的径向平面中移位 。

公开(公告)号：US06308898B1

公开(公告)日：2001-10-30

申请号：US09332268

申请日：1999-06-11

申请人： John Dorris, III ,  David Michael Smith ,  David Espineli Parekh ,  Valdis Kibens

发明人： John Dorris, III ,  David Michael Smith ,  David Espineli Parekh ,  Valdis Kibens

IPC分类号： F02K100

CPC分类号： F02K1/34

摘要： Mixing of a subsonic exhaust plume from a nozzle is induced and enhanced, and shaping of the plume is controlled, by periodic pulsed jets of fluid injected into the plume from two or more locations spaced circumferentially about the plume. The jets are pulsed out of phase relative to one another. An active flow control apparatus includes at least first and second pulsed jet nozzles circumferentially spaced apart about the exhaust plume near an exit plane of the exhaust nozzle, and a pulse generator operable to supply periodic pulses of fluid to each of the pulsed jet nozzles such that the pulses to each nozzle are out of phase relative to the pulses to the other nozzle or nozzles.

摘要翻译： 诱导和增强亚音速排气羽流从喷嘴的混合，并且通过从围绕羽流周向间隔开的两个或更多个位置注入到羽流中的周期性脉冲射流来控制羽流的成形。 射流相对于彼此脉冲异相。 主动流量控制装置包括至少第一和第二脉冲喷射喷嘴，其围绕排气喷嘴的出射面附近的排气羽流周向隔开;以及脉冲发生器，其可操作以向每个脉冲喷嘴提供周期性的脉冲脉冲，使得 到每个喷嘴的脉冲相对于其它喷嘴或喷嘴的脉冲是异相的。

公开(公告)号：US06289671B1

公开(公告)日：2001-09-18

申请号：US09377855

申请日：1999-08-20

申请人： Matvei Mikhailovich Makarov

发明人： Matvei Mikhailovich Makarov

IPC分类号： F02K100

CPC分类号： F02K9/978

摘要： Plugs for protecting internal spaces of rocket combustion chambers against moisture, dust, and other environmental factors. Each plug includes a central rod with a bracket fastened to it. The plug also includes a sleeve with radially extending structural ribs. Spring-loaded cams with rollers are securely hinged at the ends of the ribs. In addition, a spring-loaded limiter and a valve are mounted on the central rod so that they can possibly move relative to the central rod. The limiter includes a sleeve and a conical shell that are connected by rod ties. The valve includes a metal stamped conical plate that forms a gas-tight fit with the rod. A sealing ring of elastic material is positioned on a peripheral part of the plate. The set of spring-loaded cams and the limiter secure the self-mounting plug in a working position and make the valve operation independent of the operation of other plug components.

摘要翻译： 用于保护火箭燃烧室的内部空间防止湿气，灰尘和其他环境因素的插头。 每个插头都包括一个带有支架的中心杆。 塞子还包括具有径向延伸的结构肋的套筒。 具有滚子的带弹簧的凸轮牢固地铰接在肋的端部。 此外，弹簧加载的限制器和阀安装在中心杆上，使得它们可以相对于中心杆移动。 限位器包括通过杆扣连接的套筒和锥形壳体。 该阀包括与该杆形成气密配合的金属冲压锥形板。 弹性材料的密封圈定位在板的周边部分上。 一组弹簧加载的凸轮和限位器将自动安装插头固定在工作位置，使阀门操作独立于其他插头组件的操作。

公开(公告)号：US06289669B1

公开(公告)日：2001-09-18

申请号：US09257420

申请日：1999-02-25

申请人： Karl Smirra

发明人： Karl Smirra

IPC分类号： F02K100

CPC分类号： F02K9/805 ,  F02K1/00 ,  F02K9/86 ,  F02K9/88 ,  F42B10/663

摘要： A lateral-thrust control device for a four-quadrant final-phase guidance control of a missile having lateral-thrust nozzles (10) communicating with a solid-fuel gas generator (13). Each of the nozzles has a valve member (22, 38), whose open and closed states are controlled by a common actuator (12, 30) which is rotatable and axially displaceable to select one nozzle to be supplied with gas from the gas generator while the other nozzles are closed according to the required flight mode. The actuator is configured such that each of the lateral-thrust nozzles (20) can be individually controlled to be active or inactive, intermittently, and independently of one another. In one embodiment, the actuator is a cylindrical piston and in another is a conical member.

摘要翻译： 一种用于具有与固体燃料气体发生器（13）连通的侧向推力喷嘴（10）的导弹的四象限最终相位引导控制的横向推力控制装置。 每个喷嘴具有阀构件（22,38），其打开和关闭状态由公共致动器（12,30）控制，该致动器可旋转和轴向移位，以选择一个喷嘴从气体发生器供应气体，同时 其他喷嘴根据所需的飞行模式关闭。 致动器被构造成使得每个横向推力喷嘴（20）可以被单独控制为有效或不活动，间歇地且彼此独立。 在一个实施例中，致动器是圆柱形活塞，另一个是锥形构件。