专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

21. 发明申请

WO2006057653A2 INTEGRATED AIR INLET SYSTEM FOR MULTI-PROPULSION AIRCRAFT ENGINES 审中-公开
标题翻译：用于多推进飞机发动机的集成空气入口系统
公开(公告)号：WO2006057653A2
公开(公告)日：2006-06-01
申请号：PCT/US2005/004893
申请日：2005-02-16
申请人： AEROJET-GENERAL CORPORATION , BULMAN, Melvin, J. , BILLIG, Frederick, S.
发明人： BULMAN, Melvin, J. , BILLIG, Frederick, S.
IPC分类号： F02K9/78
CPC分类号： F02K7/10 , B64C30/00 , B64D33/02 , F02C7/042 , F02K7/14 , F02K7/16 , F02K9/18 , F05D2220/34 , Y10T137/0536
摘要： An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.
摘要翻译：用于空气呼吸联合循环飞机发动机的空气入口管道被内部分成用于发动机的低速和高速部件的单独的通道，并且包含一个或多个完全容纳在管道内的可移动的面板，并且枢转地在进入的空气被引导到两个通道的打开位置和其中所有进入的空气被引导到通向高速发动机的通道的关闭位置。这种集成的管道在飞行的所有阶段都使用所有进入的空气，而不改变发动机或发动机本身的空气捕获部分的几何形状，也不会使可动的前缘暴露。结果是最小的冲击波和发动机运转的高效率。

22. 发明申请

WO2009025803A1 ENERGY-DEPOSITION SYSTEMS, EQUIPMENT AND METHODS FOR MODIFYING AND CONTROLLING SHOCK WAVES AND SUPERSONIC FLOW 审中-公开
标题翻译：能量沉积系统，设备和方法，用于修改和控制冲击波和超声波流
公开(公告)号：WO2009025803A1
公开(公告)日：2009-02-26
申请号：PCT/US2008/009885
申请日：2008-08-20
申请人： KREMEYER, Kevin
发明人： KREMEYER, Kevin
IPC分类号： B64D47/00
CPC分类号： F15D1/008 , F02K7/14 , F05D2250/51 , F15D1/12 , G01M9/065 , Y02T50/672 , Y10T137/0536
摘要： Systems, equipment, and methods to deposit energy to modify and control shock waves and hypersonic or supersonic fluid flow, including systems for controlling, mitigating, and/or effecting air flow in relation to air vehicles, wind tunnels, or other assets, or the like, as well as systems, equipment, and methods for disrupting the shock structure at the inlet for the engine of an air vehicle traveling at supersonic or hypersonic speed; mitigating blast effects on vehicles; mitigating heating of throats in supersonic and hypersonic wind tunnels, as well as control the flow parameters and Mach number in their test sections.
摘要翻译：包括用于调节和控制冲击波和超音速或超音速流体流动的系统，设备和方法，包括用于控制，减轻和/或影响与航空器，风洞或其他资产有关的气流的系统，或以及用于扰乱以超音速或超音速行驶的空中交通工具的发动机入口处的冲击结构的系统，设备和方法; 减轻对车辆的爆炸影响; 减轻超音速和超音速风洞喉咙的加热，并控制其测试部分的流量参数和马赫数。

23. 发明申请

WO2008076318A3 COMBINED CYCLE INTEGRATED COMBUSTOR AND NOZZLE SYSTEM 审中-公开
标题翻译：组合式循环混合气体和喷嘴系统
公开(公告)号：WO2008076318A3
公开(公告)日：2008-10-09
申请号：PCT/US2007025522
申请日：2007-12-12
申请人： AEROJET GENERAL CO , BULMAN MELVIN J
发明人： BULMAN MELVIN J
IPC分类号： F02K7/08
CPC分类号： F02K7/18 , F02K7/10 , F02K7/14 , F02K7/16 , F05D2220/10 , Y02T50/67
摘要： An engine (20) that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine (20) is a combined cycle engine having both a booster (30) and a dual mode ramjet (DMRJ). The booster (30) and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster (30) accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air (28) delivered to the DMRJ is accelerated by primary ejector thrusters (34) that may receive oxidizer from either on-board oxidizer tanks (31 ) or from booster (30) compressor discharge air.
摘要翻译：通过节省车辆和发动机开发成本，在Hypersonic联合循环车辆上操作并产生整个所需车辆推力的发动机（20）在Mach4以下。一个这样的发动机（20）是具有增压器（30）和双模式冲压喷气发动机（DMRJ）的组合循环发动机。增压器（30）和DMRJ被一体化以提供从马赫0到超过马赫数4的有效推力。随着助力器（30）将车辆从马赫0加速到超过马赫数4，从马赫0到大约马赫数2 传送到DMRJ的进入空气（28）通过可从车载氧化剂罐（31）或增压器（30）压缩机排出空气接收氧化剂的主喷射推进器（34）加速。

24. 发明申请

WO2016157224A1 ENGINE FOR HYPERSONIC AIRCRAFTS WITH SUPERSONIC COMBUSTOR 审中-公开
标题翻译：发动机用于超级飞行员的超级飞机
公开(公告)号：WO2016157224A1
公开(公告)日：2016-10-06
申请号：PCT/IT2015/000096
申请日：2015-04-03
申请人： GABALDO, Marco , MAUTONE BARROS, Jose Eduardo
发明人： GABALDO, Marco
IPC分类号： F02C3/24 , F02C7/042 , F02K1/06 , F02K3/02 , F02K3/08 , F02K7/14 , F02K7/16 , F02K7/18
CPC分类号： F02K7/18 , F02C3/24 , F02C7/042 , F02K1/06 , F02K3/02 , F02K3/08 , F02K7/14 , F05D2220/10 , F05D2250/311
摘要： Described is a propulsion system (1) for hypersonic aircraft, having an air inlet (10) of a fluid (110), a containment duct (20) and an exhaust nozzle (30). The propulsion system (1) comprises a bypass duct (40) for a flow (100) of fluid (110), an air-breathing engine (22) and a rocket (23) configured for processing respective flows (22a, 23a) of fluid (110). The bypass duct (40), the air-breathing engine (22) and the rocket (23) are operatively associated with each other in such a way as to generate a thermodynamic-fluid interaction in a same portion of space (33) between the respective flows (40a, 22a, 23a) processed in an operating configuration of the propulsion system (1) and wherein the portion of space (33) is inside the containment duct (20).
摘要翻译：描述了一种用于超音速飞行器的推进系统（1），其具有流体（110）的空气入口（10），容纳管道（20）和排气喷嘴（30）。推进系统（1）包括用于流体（110）的流动（100）的旁通管道（40），空气呼吸发动机（22）和火箭（23），其构造成用于处理相应的流动（22a，23a）流体（110）。旁路管道（40），空气呼吸发动机（22）和火箭（23）可操作地彼此关联，以便在空间（33）的相同部分之间产生热力 - 流体相互作用在推进系统（1）的操作构造中处理的各个流（40a，22a，23a），并且其中所述空间部分（33）在所述容纳通道（20）内。

25. 发明申请

WO2009007564A2 TURBOREACTEUR POUR AERONEF 审中-公开
标题翻译：涡轮发动机
公开(公告)号：WO2009007564A2
公开(公告)日：2009-01-15
申请号：PCT/FR2008/051089
申请日：2008-06-18
申请人： AIRBUS FRANCE , BULIN, Guillaume , OBERLE, Patrick
发明人： BULIN, Guillaume , OBERLE, Patrick
IPC分类号： F02C7/14 , F02K3/06 , B64D33/08 , F02C7/12
CPC分类号： F02K7/14 , F01D9/065 , F02C7/14 , F02C7/185 , F02K3/06 , F05D2240/12 , F05D2250/32 , F05D2260/20 , F05D2260/2214 , Y02T50/67 , Y02T50/676
摘要： L'invention concerne un turboréacteur pour aéronef comportant un moteur logé dans une nacelle et au moins un échangeur thermique (13) destiné à refroidir un fluide chaud prélevé dans le système propulsif du turboréacteur avant réinjection dudit fluide chaud partiellement refroidi dans ledit système propulsif, caractérisé en ce qu'au moins un échangeur thermique (13) est un échangeur thermique radial s'étendant en partie basse du turboréacteur, au niveau d'une bifurcation inférieure (16) du turboréacteur.
摘要翻译：本发明涉及一种用于飞机的涡轮喷气发动机，其包括设置在机舱中的发动机和至少一个热交换器（13），用于冷却涡轮喷气发动机的推进系统中收集的热流体，然后重新喷射所述部分冷却热流入所述推进系统，其特征在于，至少一个热交换器（13）是在涡轮喷气发动机的下分支（16）处在涡轮喷气发动机的下部延伸的径向热交换器。

26. 发明公开

EP1916407A3 Scramjet/ramjet engine with annular isolator 审中-公开
标题翻译：冲压发动机/冲压发动机驱动用的环形绝缘体
公开(公告)号：EP1916407A3
公开(公告)日：2012-01-18
申请号：EP07254190.7
申请日：2007-10-23
申请人： United Technologies Corporation
发明人： Follett, William W. , Morrison, Calvin Q. , Goldman, Allen Lewis , Edelman, Raymond B.
IPC分类号： F02K7/10 , F02K7/14
CPC分类号： F02K7/14 , F02K7/10 , F05D2250/232 , F05D2250/41 , Y02T50/671
摘要： A dual mode scramjet engine (20) has an isolator (24) that serves to minimize combustor influence on inlet operation, a combustor (26) for operation in both ramjet and scramjet mode, and a centerbody (30) positioned within the isolator (24). The centerbody (30) has an end at an entrance to the combustor (26).

27. 发明公开

EP1718857A4 INTEGRATED AIR INLET SYSTEM FOR MULTI-PROPULSION AIRCRAFT ENGINES 有权
标题翻译：综合进气系统多个驱动飞机搭载DRIVE WORKS
公开(公告)号：EP1718857A4
公开(公告)日：2008-11-12
申请号：EP05851149
申请日：2005-02-16
申请人： AEROJET GENERAL CO
发明人： BULMAN MELVIN J , BILLIG FREDERICK S
IPC分类号： B64D33/02 , F02K99/00 , F02K7/16
CPC分类号： F02K7/10 , B64C30/00 , B64D33/02 , F02C7/042 , F02K7/14 , F02K7/16 , F02K9/18 , F05D2220/34 , Y10T137/0536
摘要： An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.

28. 发明公开

EP1916407A2 Scramjet/ramjet engine with annular isolator 审中-公开
标题翻译： Scramjet / Ramjet Antrieb mitringförmigem隔离器
公开(公告)号：EP1916407A2
公开(公告)日：2008-04-30
申请号：EP07254190.7
申请日：2007-10-23
申请人： United Technologies Corporation
发明人： Follett, William W. , Morrison, Calvin Q. , Goldman, Allen Lewis , Edelman, Raymond B.
IPC分类号： F02K7/10 , F02K7/14
CPC分类号： F02K7/14 , F02K7/10 , F05D2250/232 , F05D2250/41 , Y02T50/671
摘要： A dual mode scramjet engine (20) has an isolator (24) that serves to minimize combustor influence on inlet operation, a combustor (26) for operation in both ramjet and scramjet mode, and a centerbody (30) positioned within the isolator (24). The centerbody (30) has an end at an entrance to the combustor (26).
摘要翻译：双模式冲压喷气发动机（20）具有隔离器（24），其用于使燃烧器对入口操作的影响最小化，用于在冲压喷气和冲压喷射模式下操作的燃烧器（26）和位于隔离器（24）内的中心体（30））。中心体（30）在燃烧器（26）的入口处具有一端。

29. 发明公开

EP0663524A1 Scram-stage missile 失效
标题翻译： Staustrahlantrieb mitÜberschallverbrennungfürFlugkörper。
公开(公告)号：EP0663524A1
公开(公告)日：1995-07-19
申请号：EP94119067.0
申请日：1994-12-02
申请人： ROCKWELL INTERNATIONAL CORPORATION
发明人： Ortwerth, Paul James , Bowcutt, Kevin Gerald
IPC分类号： F02K7/14 , F02K9/64 , F02K9/52
CPC分类号： F02K9/64 , F02K7/14 , F02K9/52
摘要： A conical body scram missile having a plurality of scram engine modules (5) around the perimeter to make full use of the air flow around the body of the missile. The engine modules (5) are cooled by fuel flowing through channels in the engine walls. The engine modules produce a thrust to weight ratio of about 100 to 1.
摘要翻译：具有围绕周边具有多个冲击发动机模块（5）的锥形体卡拉姆导弹，以充分利用导弹主体周围的空气流。发动机模块（5）由流过发动机壁的通道的燃料冷却。发动机模块产生的推力重量比约为100至1.

30. 发明公开

EP2167798A2 TURBOREACTEUR POUR AERONEF 审中-公开
标题翻译：涡喷FOR A平面
公开(公告)号：EP2167798A2
公开(公告)日：2010-03-31
申请号：EP08806024.9
申请日：2008-06-18
申请人： Airbus Operations (Société par actions simplifiée)
发明人： BULIN, Guillaume , OBERLE, Patrick
IPC分类号： F02C7/14 , F02K3/06
CPC分类号： F02K7/14 , F01D9/065 , F02C7/14 , F02C7/185 , F02K3/06 , F05D2240/12 , F05D2250/32 , F05D2260/20 , F05D2260/2214 , Y02T50/67 , Y02T50/676
摘要： The invention relates to a turbojet engine for an aircraft that comprises an engine provided in a nacelle and at least one heat exchanger (13) for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting said partially-cooled hot flow into said propulsion system. The heat exchanger (13) is a radial surface heat exchanger extending in the lower portion of the turbojet engine at a lower branching (16) thereof, parallel to an outer side wall of said lower branching.

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