专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

EP2137395B1 ROCKET ENGINE LAVAL NOZZLE 有权
标题翻译：拉瓦尔一个火箭DRIVE
公开(公告)号：EP2137395B1
公开(公告)日：2010-09-22
申请号：EP08719289.4
申请日：2008-03-13
申请人： Moscow Aviation Institute
发明人： SEMENOV, Vasily, V. , SERGIENKO, Alexander, A.
IPC分类号： F02K9/82 , F02K9/97
CPC分类号： F02K1/36 , F02K1/38 , F02K9/82 , F02K9/97

2. 发明公开

EP1696116A2 Thrust vectoring using fluid jets 有权转让
标题翻译： Schubumlenkung手套Flüssigkeitsstrahlen
公开(公告)号：EP1696116A2
公开(公告)日：2006-08-30
申请号：EP06250695.1
申请日：2006-02-09
申请人： Rolls-Royce plc
发明人： Avenell, Christopher Stuart
IPC分类号： F02K1/28
CPC分类号： F02K1/002 , B64C15/02 , B64C21/04 , F02K1/006 , F02K1/28 , F02K9/82 , F05D2250/314 , F05D2270/18 , F15D1/08 , F42B10/668 , Y02T50/166
摘要： A fluid vectoring nozzle (10) comprises flow vectoring means suitable for selectively producing a fluid dynamic throat (28) in the nozzle(1 0) in a plane oblique to the axis of the nozzle (10), such that in operation fluid flow passing through the throat (28) is rotated about an axis parallel to and coincident with the plane of the throat (28). That is to say, the present invention comprises flow vectoring means suitable for selectively producing a fluid dynamic throat (28) in the nozzle (10) in a plane oblique to the axis of the nozzle (10), such that, in operation, fluid passing through the fluid dynamic throat (28) is turned towards an angle perpendicular to the plane of the throat (28). Fluid injection means are provided to inject a control fluid (26) into the nozzle (10) through a perforate region provided in at least one nozzle wall (23), thereby generating a fluid dynamic restriction (24) which initates the formation of the fluid dynamic throat (28).
摘要翻译：流体引导喷嘴（10）包括适于在倾斜于喷嘴（10）的轴线的平面中选择性地在喷嘴（10）中产生流体动态喉部（28）的流动矢量化装置，使得在操作中流体流动通过通过喉部（28）围绕与喉部（28）的平面平行并且重合的轴线旋转。也就是说，本发明包括适于在倾斜于喷嘴（10）的轴线的平面中选择性地在喷嘴（10）中产生流体动态喉部（28）的流动引导装置，使得在操作中，流体通过流体动态喉部（28）的方向转向垂直于喉部（28）平面的角度。提供流体注射装置以通过设置在至少一个喷嘴壁（23）中的穿孔区域将控制流体（26）喷射到喷嘴（10）中，从而产生流体动态限制（24），其启动流体的形成动态喉咙（28）。

3. 发明授权

EP2209981B1 TUYÈRE PROPULSIVE DE DÉTENTE D'UN JET SUPERSONIQUE DE GAZ AVEC UN FLUX SECONDAIRE D'ÉCRAN 有权
标题翻译：芬兰ÜBERSCHALLSTRAHLANTRIEBMITNEBENSTROMUMHÜLLUNG
公开(公告)号：EP2209981B1
公开(公告)日：2017-03-08
申请号：EP08853466.4
申请日：2008-11-06
申请人： Centre National d'Etudes Spatiales
发明人： BOCCALETTO, Luca
IPC分类号： F02K9/97 , F02K9/82 , F02K9/88
CPC分类号： F02K9/82 , F02K9/88 , F02K9/972

4. 发明公开

EP2103799A3 Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine 有权
标题翻译： Raketenschubdüseund Steuerungsverfahren derAbgasströmung在einem Raketentriebwerk
公开(公告)号：EP2103799A3
公开(公告)日：2013-06-26
申请号：EP08162393.6
申请日：2008-08-14
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Kimura, Tatsuya , Kawamata, Yoshihiro , Niu, Kenichi
IPC分类号： F02K9/97 , F02K9/40 , F02K9/48 , F02K9/82 , F02K1/38
CPC分类号： F02K1/38 , F02K9/48 , F02K9/58 , F02K9/82 , F02K9/972 , F05D2250/713
摘要： A rocket nozzle (8) includes a dual-bell nozzle (10) and a gas introducing section (40A, 40B, 40C, 40D) configured to introduce gas into space (80) surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle (20) bell-shaped and surrounding an upstream portion (81) of the space, and a second stage nozzle (30) bell-shaped and surrounding a downstream portion (82) of the space. The dual-bell nozzle has an inflection point (12) between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet (45, 63) provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.
摘要翻译：火箭喷嘴（8）包括双钟形喷嘴（10）和被配置为将气体引入由双钟形喷嘴包围的空间（80）中的气体引入部分（40A，40B，40C，40D）。燃烧气体在空间流动。双钟形喷嘴包括钟形的第一级喷嘴（20）并且围绕该空间的上游部分（81），并且第二级喷嘴（30）是钟形的并围绕该空间的下游部分（82）。双钟形喷嘴在第一级喷嘴和第二级喷嘴之间具有拐点（12）。气体导入部包括设置在第一级喷嘴的内壁面的气体入口（45,63）。气体从气体入口引入空间。

5. 发明公开

EP1931871A2 THRUST AUGMENTATION IN PLUG NOZZLES AND EXPANSION-DEFLECTION NOZZLES 审中-公开
标题翻译：在塞式喷嘴和扩张式喷嘴中推力增加
公开(公告)号：EP1931871A2
公开(公告)日：2008-06-18
申请号：EP06814412.0
申请日：2006-09-08
申请人： AEROJET-GENERAL CORPORATION
发明人： LAUSTEN, Merlyn , BULMAN, Melvin, J.
IPC分类号： F02K9/62
CPC分类号： F02K9/90 , F02K9/62 , F02K9/82 , F05D2240/1281
摘要： Thrust augmentation in a rocket nozzle is achieved by incorporating injectors for the introduction of unburnt fuel and oxidizer into a nozzle to combust in the nozzle and thereby supplement the primary thrust that is supplied by fuel and oxidizer that are combusted prior to entry into the nozzle. These secondary injectors are incorporated into the design of expansion-deflection nozzles and plug nozzles. In expansion-deflection nozzles, the injectors are either in the flow deflector itself or in the wall of the divergent section of the nozzle. In plug nozzles, the injectors are either in a shell of the nozzle surrounding the forward end of the centerbody or in the centerbody itself.
摘要翻译：在火箭喷嘴中的推力增加是通过结合喷嘴将未燃烧燃料和氧化剂引入喷嘴中以在喷嘴中燃烧并由此补充由进入喷嘴之前燃烧的燃料和氧化剂供应的主推力而实现的。这些二次喷射器被结合到膨胀偏转喷嘴和塞喷嘴的设计中。在膨胀偏转喷嘴中，喷射器或者位于导流板本身内，或者位于喷嘴发散部分的壁内。在塞式喷嘴中，喷射器要么位于围绕中心体前端的喷嘴壳体中，要么位于中心体本身中。

6. 发明公开

EP1402166A4 ROCKET VEHICLE THRUST AUGMENTATION WITHIN DIVERGENT SECTION OF NOZZLE 有权
标题翻译：火箭车辆采用的发散部分中排气喷管装置抗剪加固
公开(公告)号：EP1402166A4
公开(公告)日：2004-08-18
申请号：EP02749714
申请日：2002-06-28
申请人： AEROJET GENERAL CO
发明人： BULMAN MELVIN J
IPC分类号： F02K1/00 , F02K1/30 , F02K9/12 , F02K9/18 , F02K9/24 , F02K9/62 , F02K9/82 , F02K9/97 , F02K9/80
CPC分类号： F02K1/30 , F02K9/12 , F02K9/18 , F02K9/82 , F02K9/97 , F02K9/974
摘要： Augmentation of the thrust achieved by a supersonic nozzle (11) of continuous curvature is achieved by causing secondary combustion to occur in an annular region (25) of the combustion that complements the primary combustion gas (26) passing through the nozzle and maintains a wall pressure that is greater or equal to the ambient pressure at low altitudes, eliminating the negative component of the thrust in an overexpanded nozzle at takeoff.

7. 发明授权

EP0871582B1 APPARATUS AND METHOD FOR CONTROLLING THE MOTION OF A FLUID MEDIUM 失效
标题翻译：装置和方法用于控制流体介质的移动
公开(公告)号：EP0871582B1
公开(公告)日：2004-04-28
申请号：EP96941802.9
申请日：1996-12-29
申请人： Ramot at Tel-Aviv University Ltd.
发明人： SEIFERT, Avi , WYGNANSKI, Israel
IPC分类号： B64B1/36 , B64C15/02 , B63H11/10
CPC分类号： F02K9/90 , F02K9/80 , F02K9/82 , F42B10/66 , F42B10/665
摘要： This invention discloses a fluid dynamic system including a fluid medium separated from a solid medium by a solid boundary, one of which media is moving with respect to the other, apparatus for controlling the motion of the moving medium, comprising, a perturbation-producing element at solid boundary, and a drive for cyclically driving the perturbation-producing element to produce cyclical fluid perturbations in the fluid medium sufficient to alter the motion of the moving medium. A method for including a fluid medium separated from a solid medium by a solid boundary in a fluid dynamic system is also disclosed.

8. 发明公开

EP1286039A2 Raketenantrieb mit Zusatzstoffeinleitung 审中-公开
公开(公告)号：EP1286039A2
公开(公告)日：2003-02-26
申请号：EP02018851.2
申请日：2002-08-23
申请人： Weinhold, Michael
发明人： Weinhold, Michael
IPC分类号： F02K9/82
CPC分类号： F02K9/82
摘要： Die Erfindung bezieht sich auf ein Verfahren zur Erhöhung der Schubkraft von Raketenantrieben mit einer Zersetzung/Verbrennung eines Treibstoffes und einem daraus resultierenden gerichteten Abgasstrahl, welches dadurch gekennzeichnet ist, daß ein Zusatzstoff in den Abgasstrahl geleitet wird.
Die Erfindung betrifft ferner einen Raketenantrieb zur Durchführung dieses Verfahrens.
摘要翻译：推力增加过程包括将来自容器（21）的可能预热的辅助驱动物质添加到由燃烧室（11）中的驱动物质的转化或燃烧产生这种射流的火箭的排气喷射（12）。预热可使辅助物质蒸发。

9. 发明授权

EP2103799B1 Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine 有权
公开(公告)号：EP2103799B1
公开(公告)日：2018-05-23
申请号：EP08162393.6
申请日：2008-08-14
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Kimura, Tatsuya , Kawamata, Yoshihiro , Niu, Kenichi
IPC分类号： F02K9/97 , F02K9/40 , F02K9/48 , F02K9/82 , F02K1/38
CPC分类号： F02K1/38 , F02K9/48 , F02K9/58 , F02K9/82 , F02K9/972 , F05D2250/713
摘要： A rocket nozzle (8) includes a dual-bell nozzle (10) and a gas introducing section (40A, 40B, 40C, 40D) configured to introduce gas into space (80) surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle (20) bell-shaped and surrounding an upstream portion (81) of the space, and a second stage nozzle (30) bell-shaped and surrounding a downstream portion (82) of the space. The dual-bell nozzle has an inflection point (12) between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet (45, 63) provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.

10. 发明授权

EP1696116B1 Thrust vectoring using fluid jets 有权转让
标题翻译：使用流体射流的推力矢量
公开(公告)号：EP1696116B1
公开(公告)日：2018-04-11
申请号：EP06250695.1
申请日：2006-02-09
申请人： Rolls-Royce plc
发明人： Avenell, Christopher Stuart
IPC分类号： F02K1/28 , F02K1/00 , F02K9/82 , B64C15/02 , F15D1/08 , F42B10/66
CPC分类号： F02K1/002 , B64C15/02 , B64C21/04 , F02K1/006 , F02K1/28 , F02K9/82 , F05D2250/314 , F05D2270/18 , F15D1/08 , F42B10/668 , Y02T50/166
摘要： A fluid vectoring nozzle (10) comprises flow vectoring means suitable for selectively producing a fluid dynamic throat (28) in the nozzle(1 0) in a plane oblique to the axis of the nozzle (10), such that in operation fluid flow passing through the throat (28) is rotated about an axis parallel to and coincident with the plane of the throat (28). That is to say, the present invention comprises flow vectoring means suitable for selectively producing a fluid dynamic throat (28) in the nozzle (10) in a plane oblique to the axis of the nozzle (10), such that, in operation, fluid passing through the fluid dynamic throat (28) is turned towards an angle perpendicular to the plane of the throat (28). Fluid injection means are provided to inject a control fluid (26) into the nozzle (10) through a perforate region provided in at least one nozzle wall (23), thereby generating a fluid dynamic restriction (24) which initates the formation of the fluid dynamic throat (28).

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式