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31. 发明申请

WO2012094351A2 HIGHLY INTEGRATED INSIDE-OUT RAMJET 审中-公开
标题翻译：高度集成的内置RAMJET
公开(公告)号：WO2012094351A2
公开(公告)日：2012-07-12
申请号：PCT/US2012020118
申请日：2012-01-04
申请人： GURIN MICHAEL
发明人： GURIN MICHAEL
IPC分类号： F02K7/10 , F04D25/02 , F04D29/00
CPC分类号： F02K7/10
摘要： The present invention generally relates to power generation and compression methods requiring high efficiency and low capital cost. In one embodiment, the present invention relates to an inside-out ramjet having both circumferential components and radial components on a single shaft to maximize exergy efficiency and minimize system size.
摘要翻译：本发明一般涉及需要高效率和低资本成本的发电和压缩方法。在一个实施例中，本发明涉及在单个轴上具有两个圆周部件和径向部件的内向冲压式冲压件，以最大限度地提高效率并使系统尺寸最小化。

32. 发明申请

WO2010046704A3 METHOD AND SYSTEM FOR ALTERING ENGINE AIR INTAKE GEOMETRY 审中-公开
标题翻译：用于改变发动机进气几何的方法和系统
公开(公告)号：WO2010046704A3
公开(公告)日：2010-06-24
申请号：PCT/GB2009051421
申请日：2009-10-22
申请人： MBDA UK LTD , RICHARDS CLIFFORD JOHN
发明人： RICHARDS CLIFFORD JOHN
IPC分类号： F02C7/04 , F01D5/14 , F02C7/042 , F02C7/057 , F02K1/30 , F02K7/10 , F02K7/16
CPC分类号： F02C7/042 , F02C7/057 , F02K1/30 , F02K7/10 , F02K7/16
摘要： An air intake (10) for a supersonic air-breathing flight vehicle is equipped with a means (110) for introducing or injecting air (90) in order to create predetermined regions of separated flow (160) and an attendant fluid shear layer (170). This shear layer (170) forms an aerodynamic boundary for the capture flow (150) with a profile determined and optimised by appropriate injection of air (90). The aerodynamic boundary so generated replaces mechanically moveable solid surfaces used to vary the geometry of prior-art intakes. Use of introduced or injected air (90) provides the advantages of a variable geometry, but with reduced weight and reduced mechanical complexity. In some embodiments, (15) the injection of air (90) has the effect of re-energising any ingested boundary layer (140), thus obviating the conventional requirement for a bleed system to provide boundary layer control.
摘要翻译：用于超音速呼吸飞行器的进气口（10）装备有用于引入或喷射空气（90）的装置（110），以便产生预定的分离流动区域（160）和伴随的流体剪切层（170））。该剪切层（170）通过适当地注入空气（90）确定和优化的形状为捕获流（150）形成空气动力学边界。如此产生的空气动力学边界取代了用于改变现有技术摄入的几何形状的机械可移动的固体表面。使用引入或注入的空气（90）提供了可变几何形状的优点，但重量减轻，机械复杂度降低。在一些实施例中，（15）空气喷射（90）具有重新激励任何摄取的边界层（140）的作用，因此消除了渗流系统提供边界层控制的常规要求。

33. 发明申请

WO2008091307A3 CORE BURNING FOR SCRAMJET ENGINES 审中-公开
公开(公告)号：WO2008091307A3
公开(公告)日：2008-11-06
申请号：PCT/US2007022058
申请日：2007-10-15
申请人： AEROJET GENERAL CO , BULMAN MELVIN J
发明人： BULMAN MELVIN J
IPC分类号： F02K7/10
CPC分类号： F02K7/10
摘要： A pilot for a scramjet provides a flame front 28 whose arrival at the wall of the scramjet combustor 18 is delayed thereby reducing combustor 18 heat load By combining ?n-stream injection of fuel 19 with an interior pilot and a lean (fuel-poor) outer annulus, the bulk of combustion is confined to the scramjet combustor 18 center This concept, referred to as "core-burning," further reduces combustor 18 heat load One such pilot is for a two dimensional scramjet 40 effective to propel a vehicle This pilot includes a plurality of spaced apart struts 44 separated by ducts and a strut pilot 43 contained within each strut 44 A second such pilot is for an axisymmetric scramjet engine has, in sequence and in fluid communication, an air intake 16, an open bore scramjet isolator 50 and a scramjet combustor 18.
摘要翻译：用于冲击式喷气发动机的飞行员提供了一个火焰前沿28，其到达喷气式燃烧器18的壁处延迟，从而减少了燃烧器18的热负荷。通过将燃料19的喷射燃料与内部飞行员和贫（燃料不足）外部环形空间，燃烧的主体被限制在喷气式燃烧器18中心这个被称为“燃烧燃烧”的概念进一步减少了燃烧器18的热负荷。一个这样的飞行员用于有效推进车辆的二维冲击喷气发动机。包括由管道分隔的多个间隔开的支柱44和包含在每个支柱44内的支柱导向件44.第二个这样的导向装置用于轴对称冲击式喷气发动机，依次和流体连通地具有进气口16，开口冲击式喷射隔离器 50和冲击式喷射燃烧器18。

34. 发明申请

WO03071117A8 EJECTOR BASED ENGINES 审中-公开
标题翻译：基于喷射器的发动机
公开(公告)号：WO03071117A8
公开(公告)日：2007-10-25
申请号：PCT/US0304911
申请日：2003-02-18
申请人： SPACE ACCESS LLC , BOEHNLEIN JOHN , BENDOT JOSEPH , SCHOELEN FRANCIS
发明人： BOEHNLEIN JOHN , BENDOT JOSEPH , SCHOELEN FRANCIS
IPC分类号： F02C7/143 , F02K7/10 , F02K7/00 , F02K7/12 , F02K7/18 , F23R3/28
CPC分类号： F02K7/12 , F02K7/10 , F05D2260/601
摘要： The ejector based engine is, as an example in an ejector ramjet engine (1), a propulsion duct having normal augmented ramjet elements of an inlet (2), mixer (4), diffuser (5), combustor (6) and exit nozzle (8) that allow operating velocities from zero to hypersonic. At the upstream end of the mixer (4) an injector assembly (50) is mounted in the fluid flow path to form an ejector (3). The injector assembly (50) has one or more injector rings which have alternatively offset injector exhaust nozzles (53) or slots to direct fluid toward the engine internal wall (14) or the engine longitudinal axis (9) respectively to improve fluid mixing for use of a shorter mixer section. The supply of fluid to the injector exhaust nozzles (53) may be by fuel flow pumps and other elements connected to injector chambers (55) in the injector ring or by an injector combustor (15) external to the mixer (4).
摘要翻译：作为喷射器冲压喷气发动机（1）中的示例，喷射器发动机是具有入口（2），混合器（4），扩散器（5），燃烧器（6）和出口喷嘴（6）的正常增强的冲压喷气元件的推进管道（8）允许操作速度从零到超音速。在混合器（4）的上游端，喷射器组件（50）安装在流体流动路径中以形成喷射器（3）。喷射器组件（50）具有一个或多个喷射器环，其具有替代地偏置喷射器排气喷嘴（53）或狭槽以分别朝向发动机内壁（14）或发动机纵向轴线（9）引导流体，以改善流体混合使用较短的混合器部分。向喷射器排气喷嘴（53）供应流体可以通过燃料流动泵和连接到喷射器环中的喷射器腔室（55）的其它元件或由混合器（4）外部的喷射器燃烧器（15）供应。

35. 发明申请

WO2005008135A3 TRAPPED VORTEX COMBUSTOR 审中-公开
标题翻译：被捕获的VORTEX COMBUSTOR
公开(公告)号：WO2005008135A3
公开(公告)日：2005-06-09
申请号：PCT/US2004003880
申请日：2004-02-04
申请人： RAMGEN POWER SYSTEMS INC , KENDRICK DONALD , LAWLOR SHAWN P , STEELE ROBERT C
发明人： KENDRICK DONALD , LAWLOR SHAWN P , STEELE ROBERT C
IPC分类号： F01D1/02 , F01D1/32 , F02C3/16 , F02K7/00 , F02K7/10 , F23R20060101 , F23R3/18 , F23R3/20 , F23R3/28 , F23R3/50 , F23R3/58
CPC分类号： F23R3/50 , F01D1/026 , F01D1/32 , F02C3/165 , F02K7/005 , F02K7/10 , F05D2220/60 , F05D2250/25 , F23R3/18 , F23R3/28
摘要： A trapped vortex combustor for gas turbine engines. An annular combustor housing is provided having a plurality of inlet centerbodies disposed along a helical axis. The inlet centerbodies include a leading edge structure, opposing sidewalls, a pressurizable cavity, and a rear wall. Inlet centerbodies cooperate with adjacent structure and an aft bluff body to define a trapped vortex cavity combustion chamber for mixing an inlet fluid and burning fuel to form hot combustion gases. Mixing is enhanced by utilizing struts adjacent to the rear wall to create eddies in the fluid flow, and by injecting fuel and/or air in opposition to swirl created by the bulk fluid flow. Hot combustion gases are utilized in a turbine for extraction of kinetic energy, or in heat exchange equipment for recovery of thermal energy. High combustion efficiencies and less than 10 ppm emissions of oxides of nitrogen and of carbon monoxide are achieved.
摘要翻译：用于燃气涡轮发动机的驻涡燃烧室。提供环形燃烧室壳体，其具有沿着螺旋轴布置的多个入口中心体。入口中心体包括前缘结构，相对侧壁，可加压腔和后壁。入口中心体与相邻结构和后钝体合作以限定用于混合入口流体和燃烧燃料以形成热燃烧气体的驻留涡流腔燃烧室。通过利用与后壁相邻的支柱在流体流动中产生涡流，并且通过注入燃料和/或空气以对抗由散装流体流动产生的涡流而增强混合。热燃烧气体用于涡轮机中以提取动能，或用于热交换设备以回收热能。实现了高的燃烧效率和氮氧化物和一氧化碳的低于10ppm的排放。

36. 发明申请

WO2003074858A3 CHAMBRE DE COMBUSTION POUR STATORÉACTEUR ET STATORÉACTEUR POURVU D'UN TELLE CHAMBRE DE COMBUSTION 审中-公开
公开(公告)号：WO2003074858A3
公开(公告)日：2003-09-12
申请号：PCT/FR2003/000629
申请日：2003-02-27
申请人： EADS SPACE TRANSPORTATION SA , MBDA FRANCE , BOUCHEZ, Marc , FALEMPIN, François
发明人： BOUCHEZ, Marc , FALEMPIN, François
IPC分类号： F02K7/10
摘要： Selon l'invention - la peau interne (17) de ladite chambre de combustion est réalisée au moins en partie en un matériau composite thermostructural, qui est poreux pour le combustible traversant la double paroi (14) ; et - la porosité de ladite peau interne (17) est réglée pour que la proportion dudit combustible traversant ladite peau interne soit comprise entre 5% et 15% de la quantité totale de combustible apportée audit statoréacteur.

37. 发明申请

WO02026004A1 DEVICE FOR PRODUCING A PLASMA, IONISATION METHOD, USE OF SAID METHOD AND PRODUCTION PROCESSES USING SAID DEVICE 审中-公开
标题翻译：用于生产等离子体的装置，发光方法，使用方法和使用装置的生产方法
公开(公告)号：WO02026004A1
公开(公告)日：2002-03-28
申请号：PCT/FR2001/002934
申请日：2001-09-20
IPC分类号： B01J19/00 , B01J19/10 , F02C7/22 , F02K7/10 , F02M27/04 , F02M27/08 , F23C15/00 , F23C99/00 , H05H1/24
CPC分类号： F23C99/003 , B01J19/008 , B01J2219/0898 , F02M27/042 , H05H1/2475
摘要： The invention concerns the field of transformation of material and relates to a device for producing a plasma, an method for ionising material using said device, uses of the inventive method and production processes using said device. Said device is characterised in that it comprises a resonant chamber (1), an acoustic chamber (5) provided with an acoustic device (7) and a soliton chamber (8) for receiving the treated material coming from the resonant chamber (1) while simultaneously generating a recycling of outside air, said soliton chamber (8) defining, with a pulsating suction member (10) adjacent to the output of said soliton chamber (8), a space (11) producing ionised material.
摘要翻译：本发明涉及材料转化领域，涉及用于制造等离子体的装置，使用所述装置电离材料的方法，使用本发明的方法和使用所述装置的生产方法。所述装置的特征在于其包括谐振室（1），设置有声学装置（7）的声室（5）和用于接收来自谐振室（1）的处理材料的孤子室（8），同时同时产生外部空气的再循环，所述孤子室（8）用邻近所述孤子室（8）的输出端的脉动抽吸构件（10）限定产生电离材料的空间（11）。

38. 发明申请

WO00017492A1 MODULAR MULTI-PART RAIL MOUNTED ENGINE ASSEMBLY 审中-公开
标题翻译：模块化多部分铁路安装发动机总成
公开(公告)号：WO00017492A1
公开(公告)日：2000-03-30
申请号：PCT/US1999/018697
申请日：1999-08-17
IPC分类号： F01D25/28 , F02K7/10
CPC分类号： F02K7/10 , F01D25/285
摘要： A modular power plant apparatus, and method of power plant assembly. An inlet air module (200) is provided on feet which are mounted on self centering rugged linear roller guides (204) which are linearly displaceable along a track (206). When the fuel-air mixing module is retracted along the roller track, the main engine housing (209) is pivoted on an engine stand, to position the output shaft upward. An exhaust bearing plate is removable from the main rotor housing, to allow the rotating element to be removed. When exposed, hot section elements can be inspected, repaired, and replaced.
摘要翻译：一种模块化发电厂装置及发电厂组装方法。入口空气模块（200）设置在脚上，所述入口空气模块（200）安装在沿着轨道（206）可线性移位的自对中凹凸线性滚子导轨（204）上。当燃料 - 空气混合模块沿着滚轮轨道缩回时，主发动机壳体（209）在发动机支架上枢转，以将输出轴定位在上方。排气轴承板可从主转子壳体移除，以允许旋转元件被移除。暴露时，可以对热段元件进行检查，维修和更换。

39. 发明申请

WO99007988A1 EJECTOR RAMJET ENGINE 审中-公开
标题翻译：喷射器喷射发动机
公开(公告)号：WO99007988A1
公开(公告)日：1999-02-18
申请号：PCT/US1998/016431
申请日：1998-08-07
IPC分类号： F02K7/10 , F02K7/16 , F02K7/12
CPC分类号： F02K7/16
摘要： The ejector ramjet engine (1) is a propulsion duct having normal augmented ramjet elements of an inlet (2), mixer (4), diffuser (5), combustor (6) and exit nozzle (8). At the upstream end of the mixer (4) an injector assembly (10) is mounted in the fluid flow path to form an ejector (3). The injector assembly (10) has one or more injector rings (11) which have alternatively offset injector exhaust nozzles (13) or slots to direct fluid toward the engine internal wall (14) or the engine longitudinal axis (9) respectively to improve fluid mixing for use of a shorter mixer (4) section. The supply of fluid to the injector exhaust nozzles (13) may be by fuel flow pumps (26) and other elements connected to injector chambers (25) in the injector ring (11) or by an injector combustor (15) external to the mixer (4). A movable plug (24) is mounted on the center body fairing (17) to provide adjustment for varying velocity and pressure conditions within the engine (1) over the operating environment. This velocity/pressure regulation results in increased engine thrust and specific impulse performance. The diffuser (5) has guide vanes (19) to allow more rapid diffusion of the fluid flow.
摘要翻译：喷射器冲压喷气发动机（1）是具有入口（2），混合器（4），扩散器（5），燃烧器（6）和出口喷嘴（8）的普通增强冲压喷气元件的推进管道。在混合器（4）的上游端，喷射器组件（10）安装在流体流动路径中以形成喷射器（3）。喷射器组件（10）具有一个或多个喷射器环（11），其相应地偏置喷射器排气喷嘴（13）或狭槽以分别引导流体朝向发动机内壁（14）或发动机纵向轴线（9），以改善流体混合使用较短的混合器（4）部分。向喷射器排气喷嘴（13）供应流体可以通过燃料流量泵（26）和连接到喷射器环（11）中的喷射室（25）的其它元件或由混合器外部的喷射器燃烧室（15）（4）。可移动塞（24）安装在中心主体整流罩（17）上，以在操作环境下提供发动机（1）内的变化的速度和压力条件的调整。这种速度/压力调节导致发动机推力和比冲击性能的提高。扩散器（5）具有导向叶片（19），以允许流体流动更快地扩散。

40. 发明申请

WO2018226269A1 FLIGHT VEHICLE AIR BREATHING PROPULSION SYSTEM WITH ISOLATOR HAVING OBSTRUCTION 审中-公开
公开(公告)号：WO2018226269A1
公开(公告)日：2018-12-13
申请号：PCT/US2018/018745
申请日：2018-02-20
申请人： RAYTHEON COMPANY
发明人： CICCHINI, Nicholas, P.
IPC分类号： F02K7/10 , B64D33/02 , F02C7/04
摘要： A flight vehicle has a propulsion system that includes an air inlet, an isolator (or diffuser) downstream of the air inlet, and a combustor downstream of the isolator. The isolator includes an obstruction that protrudes inwardly from an inner wall of the isolator, into the flow channel in which air flows through the isolator. The obstruction diverts the flow to either side of it. Downstream of the obstruction the flow on either side of the obstruction comes together again, leading to mixing of the flow, for example including mixing of low energy and boundary layer flow with high energy flow. This mixing of flow may make for a more uniform flow at the exit of the isolator. In addition the obstruction may help fix the location of shocks within the isolator, providing longer flow mixing length in the isolator.

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