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公开(公告)号：US06648268B2
公开(公告)日：2003-11-18
申请号：US10074710
申请日：2002-02-13
申请人： Anthony A. duPont
发明人： Anthony A. duPont
IPC分类号： B64C2900
摘要： A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.
摘要翻译： 垂直起飞和陆地（VTOL）喷气式飞机可能有一架喷气发动机安装在飞机的前部。 推力偏转组件可以设置在喷气发动机的后方，并且包括用于在飞行器的垂直飞行期间偏转推力的级联和控制箱。 通过操纵级联和控制箱，可以控制垂直飞行期间飞行器的滚动，偏航和俯仰。 此外，可以提供副翼，方向舵和电梯，用于在前进飞行期间控制滚动，偏航和俯仰。 还提供了一种先导控制输入装置，其接收关于飞行器的期望的滚动，偏航和俯仰的导频输入。 飞行员控制输入可操作地与控制混合器相关联，控制混合器根据飞行器的期望的滚动，偏航和俯仰来控制控制箱，副翼，方向舵和电梯。 因此，飞行员使用相同的控制输入装置进行垂直和前进飞行。
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公开(公告)号：US20030150954A1
公开(公告)日：2003-08-14
申请号：US10074710
申请日：2002-02-13
发明人： Anthony A. duPont
IPC分类号： B64C029/00
摘要： A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.
摘要翻译： 垂直起飞和陆地（VTOL）喷气式飞机可能有一架喷气发动机安装在飞机的前部。 推力偏转组件可以设置在喷气发动机的后方，并且包括用于在飞行器的垂直飞行期间偏转推力的级联和控制箱。 通过操纵级联和控制箱，可以控制垂直飞行期间飞行器的滚动，偏航和俯仰。 此外，可以提供副翼，方向舵和电梯，用于在前进飞行期间控制滚动，偏航和俯仰。 还提供了一种先导控制输入装置，其接收关于飞行器的期望的滚动，偏航和俯仰的导频输入。 飞行员控制输入可操作地与控制混合器相关联，控制混合器根据飞行器的期望的滚动，偏航和俯仰来控制控制箱，副翼，方向舵和电梯。 因此，飞行员使用相同的控制输入装置进行垂直和前进飞行。
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公开(公告)号：US5172546A
公开(公告)日：1992-12-22
申请号：US615048
申请日：1990-11-19
申请人： Jack R. Shekleton , Colin Rodgers
发明人： Jack R. Shekleton , Colin Rodgers
摘要： In order to establish a larger dome height to thereby increase combustion volume within the same turbine engine envelope, the inner wall region of an annular combustor is formed to define a thrust nozzle which in turn provides an enhanced combustion zone. The turbine engine will include a rotary compressor and a turbine wheel coupled to the rotary compressor for driven movement thereof along with an annular nozzle proximate the turbine wheel for directing gases of combustion thereat. The annular combustor will be disposed about the turbine wheel and defined by a radially extending wall region connecting the inner wall region to an outer wall region such that the annular combustor has a combustion zone upstream of the annular nozzle and a dilution air zone intermediate the annular nozzle and the combustion zone. The turbine engine will operate such that the annular combustor combusts fuel from a fuel source and air from the rotary compressor to generate the gases of combustion which are directed at the turbine wheel by the annular nozzle for driven movement of the turbine wheel and the rotary compressor. By reason of the thrust nozzle being axially adjacent the turbine wheel and radially inwardly of the annular combustor, the turbine engine has a generally annular expanded combustion zone relative to the dilution zone within the same turbine engine envelope.
摘要翻译： 为了建立更大的圆顶高度，从而增加同一涡轮发动机外壳内的燃烧体积，环形燃烧器的内壁区域形成为限定了一个推进喷嘴，其又提供了增强的燃烧区域。 涡轮发动机将包括旋转压缩机和联接到旋转式压缩机的涡轮机叶轮，用于与靠近涡轮机叶轮的环形喷嘴一起被驱动运动，用于引导燃烧气体。 环形燃烧器将围绕涡轮机轮设置并且由连接内壁区域到外壁区域的径向延伸的壁区域限定，使得环形燃烧器具有在环形喷嘴上游的燃烧区域和在环形燃烧器的中间的稀释空气区域 喷嘴和燃烧区。 涡轮发动机将操作，使得环形燃烧器燃烧来自燃料源的燃料和来自旋转压缩机的空气，以产生通过环形喷嘴引导到涡轮机叶轮的燃烧气体，用于涡轮机叶轮和旋转压缩机的驱动运动 。 由于推力喷嘴轴向地邻近涡轮机叶轮并且环形燃烧器的径向向内，涡轮发动机相对于同一涡轮机发动机外壳内的稀释区域具有大致环形的扩展燃烧区域。
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公开(公告)号：US09551293B2
公开(公告)日：2017-01-24
申请号：US14001998
申请日：2012-03-02
CPC分类号： F02K1/00 , B64C23/00 , B64C23/005 , F02K99/00 , F03H99/00 , Y02T50/672
摘要： A replaceable thrust generating structure for an air vehicle, which includes one or more mounts, which are attachable to the air vehicle, and a thrust generating structure attached to each of the one or more mounts, and wherein the thrust generating structure includes an NMSET element.
摘要翻译： 一种用于空中交通工具的可替换的推力产生结构，其包括一个或多个可附接到所述空中车辆的支座，以及附接到所述一个或多个支架中的每一个的推力发生结构，并且其中所述推力产生结构包括NMSET元件 。
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公开(公告)号：US20160195038A1
公开(公告)日：2016-07-07
申请号：US14817611
申请日：2015-08-04
CPC分类号： F02K1/78 , B64D29/00 , B64D29/02 , B64D29/04 , F02C3/04 , F02K1/00 , F02K1/36 , F02K1/40 , F02K1/52 , F02K1/82 , F02K3/06 , F02K3/077
摘要： A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.
摘要翻译： 用于燃气涡轮发动机的机舱包括限定中心轴线并具有径向向外表面和径向向内表面的环形主体。 径向向内表面的后部包括轴向延伸的收敛发散出口。 轴向延伸的二次管道穿过会聚发散出口喷嘴中的机舱。 轴向延伸的次级管道包括在收敛发散出口喷嘴的收敛部分处的入口和在会聚发散出口喷嘴的发散部分处的出口。
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16.发明申请FAN FOR A MULTI-FLOW TURBOSHAFT ENGINE, AND TURBOSHAFT ENGINE EQUIPPED WITH SUCH A FAN 审中-公开多流量涡轮发动机的风扇，以及配备这种风扇的涡轮发动机公开(公告)号：US20160032734A1
公开(公告)日：2016-02-04
申请号：US14776300
申请日：2014-03-04
申请人： SNECMA
CPC分类号： F01D5/26 , F01D1/06 , F01D5/22 , F01D5/3007 , F01D5/323 , F01D9/041 , F01D11/008 , F02K1/00 , F02K3/00 , F04D29/322 , F04D29/668 , F05D2220/34 , F05D2220/36 , F05D2230/644 , F05D2240/35 , F05D2260/30 , F05D2260/96
摘要： The fan comprises a fan disk able to be rotationally driven about a longitudinal axis and provided at the periphery with radial blades each comprising a root slideably engaged in a groove of the disk and, on the outside thereof, a vane, platforms surrounding the disk being interposed between the radial blades. Advantageously, the fan additionally comprises shock-absorbing wedges which are arranged tangentially at the exterior periphery of said disk underneath the platforms and between two roots of adjacent radial blades, each wedge being in tangential contact with the two adjacent blades.
摘要翻译： 所述风扇包括能够围绕纵向轴线旋转地驱动的风扇盘，并且在周边处设置有径向叶片，每个叶片包括可滑动地接合在盘的凹槽中的根部，并且在其外侧具有叶片，围绕盘的平台 介于径向叶片之间。 有利地，风扇另外包括缓冲楔形件，其相切地布置在平台下方的盘的外周边处，并且在相邻的径向叶片的两根之间，每个楔形件与两个相邻的刀片切向接触。
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公开(公告)号：US09032705B2
公开(公告)日：2015-05-19
申请号：US12578341
申请日：2009-10-13
CPC分类号： F03H1/0081 , F02K1/00 , F02K1/28 , F02K7/00 , F02K7/10 , F02K9/00 , F03H1/00 , F05D2210/12 , F05D2220/10 , F05D2220/34
摘要： The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject matter compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field and can also be extracted in the form of mechanical work.
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公开(公告)号：US20150033747A1
公开(公告)日：2015-02-05
申请号：US14363508
申请日：2012-12-04
申请人： SNECMA
发明人： Matthieu Leyko , Jean Bertucchi , Mathieu Gaillot
IPC分类号： F02K1/00
CPC分类号： F02K1/00 , F02K1/82 , F02K3/06 , F05D2250/71
摘要： A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.
摘要翻译： 涡轮发动机会聚发散喷嘴，包括环形中心元件和环形盖，该环形中心元件和环形盖同轴地布置在中心元件周围，以与中心元件配合以限定用于来自发动机的气流的环形流动通道。 在喉部和喷嘴的喷射部分之间，中心元件和帽在纵向截面中呈现相应的内部轮廓，该曲线由具有相同绝对值相同的曲率半径的曲线建模。
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19.发明申请THREADED ROD FOR SYSTEM FOR DEPLOYING A DEPLOYABLE DIVERGENT SEGMENT OF A THRUSTER 有权用于分配一个可分配的分流器的系统的螺线管公开(公告)号：US20140131481A1
公开(公告)日：2014-05-15
申请号：US14080009
申请日：2013-11-14
申请人： SNECMA
发明人： Jacques LELONG
IPC分类号： F02K1/08
CPC分类号： F02K1/08 , B23Q5/40 , B23Q11/0875 , F02K1/00 , F02K1/008 , F02K1/06 , F02K1/09 , F02K1/10 , F02K1/52 , F02K9/00 , F02K9/84 , F02K9/97 , F02K9/976 , F05D2250/42 , F16H25/2204 , F16H25/2418 , F16H2025/2037 , F16H2025/204 , F16H2025/209
摘要： The divergent segment comprises a stationary divergent portion and a movable divergent portion suitable for occupying a retracted position and a deployed position. The threaded rod has a head suitable for being supported by a support secured to the stationary divergent portion in cooperation with rotary drive means for driving the threaded rod in rotation, and a tip suitable for being inserted in a holder sleeve secured to the stationary divergent portion. The threaded rod is suitable for co-operating with a nut secured to the movable divergent portion so that rotation of said rod causes the movable divergent portion to move. The tip presents an enlargement having at least one groove passing axially therethrough.
摘要翻译： 发散段包括固定的发散部分和适于占据缩回位置和展开位置的可移动发散部分。 所述螺纹杆具有适于由固定在所述固定发散部分上的支撑件支撑的头部，所述支撑件用于旋转驱动所述螺杆的旋转驱动装置，以及适于插入固定到所述固定发散部分的保持套筒中的尖端 。 螺杆适于与固定在可移动发散部分上的螺母配合，使得所述杆的旋转使可动发散部分移动。 尖端具有至少一个通过轴向穿过的槽的放大图。
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公开(公告)号：US20130336772A1
公开(公告)日：2013-12-19
申请号：US14003180
申请日：2012-03-02
IPC分类号： F01D25/24
CPC分类号： F01D25/24 , B64D33/04 , F02K1/00 , F02K1/82 , F05D2250/71 , F05D2250/711 , Y02T50/671
摘要： A turbine engine pipe having a longitudinal axis, which, at an upstream end thereof, includes an outer wall and a core, only an upstream portion of which is surrounded by the outer wall. The boundary between the upstream portion and a downstream portion is defined by the intersection between the core and the surface formed by bisectors of acute angles formed by straight lines perpendicular to the outer wall and straight lines perpendicular to an outer surface of the core passing through the downstream end of the outer wall. The outer surface of the downstream portion of the core has a sharply curved convex region close to the boundary, the region having a radius of curvature in a radial plane of less than 30 times the radius of the core at the boundary, and a first slightly curved region between the boundary and the sharply curved convex region.
摘要翻译： 一种具有纵向轴线的涡轮发动机管道，其在其上游端包括外壁和芯部，只有其上游部分被外壁包围。 上游部分和下游部分之间的边界由芯和由垂直于外壁的直线形成的锐角的平分线形成的表面和垂直于芯的外表面的直线形成的表面之间的交点限定， 外壁的下游端。 芯的下游部分的外表面具有接近边界的急剧弯曲的凸起区域，该区域在径向平面中的曲率半径小于边界处的芯的半径的30倍，并且第一稍微 边界与锐曲的凸区域之间的弯曲区域。
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