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1. 发明公开

EP1009927A1 EJECTOR RAMJET ENGINE 有权
标题翻译：带喷射冲压发动机
公开(公告)号：EP1009927A1
公开(公告)日：2000-06-21
申请号：EP98938440.9
申请日：1998-08-07
申请人： Space Access, L.L.C. , Boehnlein, John J. , Bendot, Joseph G.
发明人： BOEHNLEIN, John, J. , BENDOT, Joseph, G.
IPC分类号： 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.

2. 发明公开

EP1163152A4 PAYLOAD CARRY AND LAUNCH SYSTEM 有权
标题翻译：系统换着穿，启动有效载荷
公开(公告)号：EP1163152A4
公开(公告)日：2004-03-03
申请号：EP99972835
申请日：1999-12-29
申请人： SPACE ACCESS L L C , SCOTT HARRY , WURST STEPHEN G
发明人： SCOTT HARRY , WURST STEPHEN G
IPC分类号： B64C30/00 , B64G1/00 , B64G1/14 , B64G1/40 , F02K7/10 , F02K7/12 , F02K9/50 , F02K9/80
CPC分类号： B64G1/401 , B64G1/005 , B64G1/007 , B64G1/14 , B64G1/402 , F02K7/10 , F02K7/12 , Y02T50/672
摘要： The reusable space launch system (1) embodiment has a first stage vehicle or aerospacecraft (50), a second stage vehicle or reusable spacecraft (51) and a third stage vehicle or reusable orbit transfercraft (52). All the stages have the basic aerodynamic vehicle elements of a fuselage, wings, and tail, with the incorporation of control surfaces to supply lift, stability and control. The aerospacecraft (50) is configured to use ejector ramjet engines (18) for powered flight and includes equipment to capture air to supplement oxidizer for the ejector ramjet engine (18) during take-off and extreme high altitude. In order to optimize aerospacecraft (50) performance in a pull up movement to exit the sensible atmosphere, the aerospacecraft (50) may include auxiliary ascent rocket engines (116).

3. 发明公开

EP1590564A1 JET EJECTOR AND METHOD OF ALTERING FLUID FLOW 审中-公开
标题翻译：喷射泵和方法改变流体流量
公开(公告)号：EP1590564A1
公开(公告)日：2005-11-02
申请号：EP04701834.6
申请日：2004-01-13
申请人： THE TEXAS A & M UNIVERSITY SYSTEM
发明人： HOLTZAPPLE, Mark, T. , REDINIOTIS, Othon
IPC分类号： F02K7/12
CPC分类号： F02K7/12 , F02C3/32 , F05D2250/292 , F05D2250/311 , F05D2260/601 , Y02T50/671
摘要： A system for altering fluid flow includes a main body having a first fluid flowing therethrough, a plurality of conduits disposed within the main body to form a plurality of flow paths, and a nozzle directing a second fluid through the innermost conduit. The second fluid has a greater velocity than the first fluid. The second fluid successively entrains the first fluid flowing through the flow paths in such a manner that the portion of the first fluid flowing through the innermost flow path existing between the innermost conduit and its adjacent conduit is entrained first and the portion of the first fluid flowing through the outermost flow path existing between the outermost conduit and the main body is last.

4. 发明公开

EP0370209A1 Engine for low-speed to hypersonic vehicles 失效
标题翻译： AntriebfürFahrzeuge von langsamer bis hypersonischer Schnelligkeit。
公开(公告)号：EP0370209A1
公开(公告)日：1990-05-30
申请号：EP89118336.0
申请日：1989-10-03
申请人： THE BOEING COMPANY
发明人： Klees, Garry W. , Sloan, Mark L. , Thornock, Russel L.
IPC分类号： F02K7/12
CPC分类号： F02K7/12 , Y02T50/671
摘要： A jet engine for use in a hypersonic aircraft. A fuel rich injectant is injected into the mixing zone of a duct at a substantial downstream angle to form an ejector. The temperature of the injectant is sufficiently low that spontaneous combustion of the injectant is delayed until the injectant reaches the combustion zone of the duct. In order to prevent combustion from propagating upstream from the combustion zone, the equivalence ratio of the mixture of injectant and ambient air flowing along the wall of the duct is maintained at a relatively high value, and the velocity profile of the flow along the wall of the duct is maintained at a relatively high value.
摘要翻译：用于超音速飞机的喷气发动机。将燃料丰富的注射剂以大体下游角度注入管道的混合区域中以形成喷射器。注射剂的温度足够低，使得注射剂的自发燃烧被延迟直到注射剂到达管道的燃烧区域。为了防止燃烧从燃烧区域的上游传播，沿着管道壁流动的注入剂和环境空气的混合物的当量比保持在相对高的值，并且沿着壁的流动的流动的速度分布导管保持在较高的值。

5. 发明公开

EP1009927A4 EJECTOR RAMJET ENGINE 有权
标题翻译：带喷射冲压发动机
公开(公告)号：EP1009927A4
公开(公告)日：2003-06-11
申请号：EP98938440
申请日：1998-08-07
申请人： SPACE ACCESS L L C , BOEHNLEIN JOHN J , BENDOT JOSEPH G
发明人： BOEHNLEIN JOHN J , BENDOT JOSEPH G
IPC分类号： F02K7/10 , F02K7/16 , F02K7/12 , F02K9/52
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.

6. 发明公开

EP0367619A1 Gas compressor for jet engine 失效
标题翻译： Kompressorfürein Strahltriebwerk。
公开(公告)号：EP0367619A1
公开(公告)日：1990-05-09
申请号：EP89311394.4
申请日：1989-11-03
申请人： Hartman, Neil Warren , F & L Development Corporation
发明人： Hartman, Neil Warren
IPC分类号： F02K7/12
CPC分类号： F02K7/12
摘要： A gas compressor is provided which can be utilized in a jet engine for propulsion of a flight vehicle at velocities ranging from static to very high Mach numbers. The jet engine includes a housing with an inlet, a mixing chamber in fluid communication with the inlet, a diffuser section in fluid communication with the mixing chamber, a combustion chamber in fluid communication with the diffuser section and an outlet in communication with the combustion chamber. Auxiliary gas injection nozzles located downstream of the mixing chamber direct a high velocity gas stream toward the outlet to induce a region of sufficiently low pressure within the mixing chamber to cause a supersonic flow of gas from the inlet section through the mixing chamber. Cryogenic fuel is injected into the mixing chamber to modify the stagnation enthalpy, pressure and temperature of the supersonic flow therethrough. Fuel is injected into the combustion chamber where the mixture of the compressed air flow from the diffuser and the fuel is ignited to produce thrust. The outlet is adjustable to provide the amount of back pressure required in the combustion chamber for stable operation.
摘要翻译：提供了一种气体压缩机，其可以用于喷气发动机中，用于以从静态到非常高的马赫数的速度推进飞行器车辆。喷气发动机包括具有入口的壳体，与入口流体连通的混合室，与混合室流体连通的扩散器部分，与扩散器部分流体连通的燃烧室和与燃烧室连通的出口。位于混合室下游的辅助气体注入喷嘴将高速气体流引向出口，以在混合室内引入足够低的压力区域，以引起来自入口部分的气体超音速流过混合室。将低温燃料注入到混合室中以改变其中超声速流动的滞留焓，压力和温度。燃料被喷射到燃烧室中，其中来自扩散器和燃料的压缩空气的混合物被点燃以产生推力。出口是可调节的，以提供燃烧室中所需的背压的量以使其稳定运行。

7. 发明公开

EP2264296A3 System for altering fluid flow 审中-公开
标题翻译：装置，用于改变流体流
公开(公告)号：EP2264296A3
公开(公告)日：2011-12-07
申请号：EP10011400.8
申请日：2004-01-13
申请人： The Texas A&M University System
发明人： Hotzapple, Mark T. , Rediniotis, Othon
IPC分类号： F02C3/32 , F02K7/12
CPC分类号： F02K7/12 , F02C3/32 , F05D2250/292 , F05D2250/311 , F05D2260/601 , Y02T50/671
摘要： A system for altering fluid flow includes a main body having a first fluid flowing therethrough, a plurality of conduits disposed within the main body to form a plurality of flow paths, and a nozzle directing a second fluid through the innermost conduit. The second fluid has a greater velocity than the first fluid. The second fluid successively entrains the first fluid flowing through the flow paths in such a manner that the portion of the first fluid flowing through the innermost flow path existing between the innermost conduit and its adjacent conduit is entrained first and the portion of the first fluid flowing through the outermost flow path existing between the outermost conduit and the main body is last.

8. 发明授权

EP1009927B1 EJECTOR RAMJET ENGINE 有权
标题翻译：带喷射冲压发动机
公开(公告)号：EP1009927B1
公开(公告)日：2005-03-16
申请号：EP98938440.9
申请日：1998-08-07
申请人： Space Access, L.L.C. , Boehnlein, John J. , Bendot, Joseph G.
发明人： BOEHNLEIN, John, J. , BENDOT, Joseph, G.
IPC分类号： F02K7/12 , F02K7/10 , F02K9/52
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.

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