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1. 发明申请

US20040134195A1 Ramjet engine combustion chamber and ramjet engine equipped with same 有权
标题翻译：喷气发动机燃烧室和配备相同的冲压式发动机
公开(公告)号：US20040134195A1
公开(公告)日：2004-07-15
申请号：US10476648
申请日：2003-11-04
发明人： Marc Bouchez , Francois Falempin
IPC分类号： F02K007/10
CPC分类号： F02K7/10 , F02K9/64
摘要： The invention concerns a combustion chamber whereof the inner wall (17)is made at least partly of a thermostructural composite material, which is porous to the fuel passing through the double wall (14); and the porosity of said inner wall (17) is adjusted so that the proportion of said fuel passing through said inner skin ranges between 5% and 15% of the total amount of fuel input in said ramjet engine.
摘要翻译：本发明涉及一种燃烧室，其中内壁（17）至少部分地由热结构复合材料制成，其对通过双壁（14）的燃料是多孔的; 并且调整所述内壁（17）的孔隙率，使得通过所述内表皮的所述燃料的比例在所述冲压式喷气发动机中输入的燃料总量的5％至15％之间。

2. 发明申请

US20030014961A1 Compact rotary ramjet engine with rapidly interchangeable cartridge containing hot section rotating elements 审中-公开
标题翻译：紧凑型旋转冲压喷气发动机，具有快速可互换的墨盒，包含热部分旋转元件
公开(公告)号：US20030014961A1
公开(公告)日：2003-01-23
申请号：US09912244
申请日：2001-07-23
申请人： RAMGEN POWER SYSTEMS, INC.
发明人： Shawn P. Lawlor , Steve B. Kushnick
IPC分类号： F02K007/10
CPC分类号： F01D25/162 , F01D1/04 , F01D25/28
摘要： A rotary ramjet engine with rapidly replaceable rotating cartridge. A rotary ramjet engine is provided operating with replaceable rotating cartridge. The rotating cartridge includes a rotor and shaft mounted for rotary motion with respect to an engine case, and a first and second bearing package. The engine has an inlet duct assembly including bearing support structures from which the rotating cartridge is rotatably supported. A hot section assembly is sealingly but releaseably affixed to the inlet duct assembly. By disengaging the hot section assembly from the inlet duct assembly, and moving the hot section assembly from an operating position to an inspection position along a convenient slide track, space is provided for inspection and/or removal and reinstallation of the rotating cartridge.
摘要翻译：具有快速更换的旋转筒的旋转冲压喷气发动机。提供旋转冲压喷气发动机，其具有可更换的旋转筒。旋转筒包括相对于发动机壳体旋转运动的转子和轴以及第一和第二轴承组件。发动机具有入口管道组件，其包括轴承支撑结构，旋转筒可旋转地支撑在该支撑结构上。热段组件密封地但是可释放地固定到入口管道组件。通过使热段组件与入口管道组件脱离接合，并且将热部分组件从操作位置沿着便利的滑动轨道移动到检查位置，提供空间用于检查和/或移除和重新安装旋转筒。

3. 发明申请

US20030182928A1 Scram jet engine design 失效
标题翻译：喷气式发动机设计
公开(公告)号：US20030182928A1
公开(公告)日：2003-10-02
申请号：US10112635
申请日：2002-03-28
发明人： Mark A. Sillence , Daniel P. Guinan , Dennis J. Nemecek , Costante Salvador , Henry K. Webster , Thomas B. Fortin , Sergio Rinella , Ravi K. Nigam
IPC分类号： F02K007/10
CPC分类号： F02K7/14 , Y02T50/672
摘要： The present invention relates to a scram jet engine for use with a hypersonic vehicle. The scram jet engine has an upper boundary wall, a lower boundary wall, and a plurality of side walls defining an inner air flowpath. The walls are formed by a plurality of tubular heat exchanger panels. Each of the heat exchanger panels comprises a plurality of structural panels, each having a plurality of cooling passages, joined together. In the scram jet engine of the present invention, fuel may be used as a coolant and supplied to the cooling passage.
摘要翻译：本发明涉及一种与超音速车辆一起使用的冲击式发动机。冲击式喷气发动机具有上边界壁，下边界壁和限定内部空气流动路径的多个侧壁。壁由多个管状热交换器板形成。每个热交换器面板包括多个结构面板，每个结构面板具有连接在一起的多个冷却通道。在本发明的冲击式发动机中，燃料可以用作冷却剂并被供应到冷却通道。

4. 发明申请

US20040128977A1 Multi-mode pulsed detonation propulsion system 失效
标题翻译：多模脉冲爆震推进系统
公开(公告)号：US20040128977A1
公开(公告)日：2004-07-08
申请号：US10337920
申请日：2003-01-07
发明人： Donald R. Wilson , Frank K. Lu
IPC分类号： F02K007/10
CPC分类号： F02K7/02 , F02K7/08 , F02K7/20 , Y02T50/671
摘要： A multi-mode propulsion system for potential application to hypersonic and aerospace planes. The system can employ various propulsion modes at various points in time, with the propulsion system employed at a given point in time being selected according to the velocity of the inlet airflow. In one embodiment, the propulsion system of the present invention has an ejector-augmented pulsed detonation rocket propulsion mode, a pulsed normal detonation wave engine mode, a steady oblique detonation wave engine mode, and a pure pulsed detonation rocket mode.
摘要翻译：一种用于潜在应用于超音速和航空航天飞机的多模式推进系统。该系统可以在各个时间点采用各种推进模式，根据入口气流的速度选择在给定时间点采用的推进系统。在一个实施例中，本发明的推进系统具有喷射器增强的脉冲爆震火箭推进模式，脉冲正常爆震波发动机模式，稳定的斜引爆波发动机模式和纯脉冲爆轰火箭模式。

5. 发明申请

US20030154720A1 Ejector based engines 失效
标题翻译：基于喷射器的发动机
公开(公告)号：US20030154720A1
公开(公告)日：2003-08-21
申请号：US10081343
申请日：2002-02-20
发明人： John Boehnlein , Joseph Bendot , Francis Schoelen
IPC分类号： F02K007/10
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, a propulsion duct having normal augmented ramjet elements of an inlet, mixer, diffuser, combustor and exit nozzle that allow operating velocities from zero to hypersonic. At the upstream end of the mixer an injector assembly is mounted in the fluid flow path to form an ejector. The injector assembly has one or more injector rings which have alternatively offset injector exhaust nozzles or slots to direct fluid toward the engine internal wall or the engine longitudinal axis respectively to improve fluid mixing for use of a shorter mixer section. The supply of fluid to the injector exhaust nozzles may be by fuel flow pumps and other elements connected to injector chambers in the injector ring or by an injector combustor external to the mixer.
摘要翻译：作为喷射器冲压喷气发动机中的示例，喷射器发动机具有允许操作速度从零到超音速的入口，混合器，扩散器，燃烧器和出口喷嘴的正常增强的冲压喷气元件的推进通道。在混合器的上游端，喷射器组件安装在流体流动路径中以形成喷射器。喷射器组件具有一个或多个喷射器环，其相应地偏置喷射器排气喷嘴或狭槽以分别朝向发动机内壁或发动机纵向轴线引导流体，以改善流体混合以使用较短的混合器部分。向喷射器排气喷嘴供应流体可以通过燃料流量泵和连接到喷射器环中的喷射室的其它元件或由混合器外部的喷射器燃烧器供应。

6. 发明申请

US20040050063A1 Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance 有权
标题翻译：紧凑型轻型冲压喷气发动机，结合旋转增强燃烧，性能提高
公开(公告)号：US20040050063A1
公开(公告)日：2004-03-18
申请号：US10360469
申请日：2003-02-06
发明人： Stephen N. Schmotolocha , Robert J. Pederson , Calvin Q. Morrison JR. , Raymond B. Edelman , Donald H. Morris
IPC分类号： F02K007/10
CPC分类号： F23C7/006 , F23C9/006 , F23C2900/09002 , F23R3/14 , F23R3/20 , F23R3/22 , F23R3/286 , Y02T50/675
摘要： A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and an inner central recirculation zone, both of which are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers and stabilizes flame propagation and accelerates combustion throughout the entire combustor. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency and thrust performance.
摘要翻译：一种冲压喷气发动装置，其利用新颖的涡流发生器，根据需要快速有效地雾化，蒸发并将燃料混合到氧化剂中。涡流发生器将氧化剂流转化为引入燃料的湍流三维流场。涡流发生器影响环形外再循环区域和内中心再循环区域，两者都以向后流动的方式构造，其将热和燃烧副产物运送到上游，在其上用于连续点燃相邻剪切中的可燃燃料/氧化剂混合物层并稳定火焰传播并加速整个燃烧室的燃烧。涡流发生器提供平稳的燃烧，没有不稳定性和最小的总压力损失，并且能够显着降低燃烧器的L / D比。其他优点包括简单性，可靠性，广泛的可燃性极限和高燃烧效率和推力性能。

7. 发明申请

US20040050062A1 SHUT-OFF SYSTEM FOR AN ORIFICE OF A DUCT, PARTICULARLY FOR AN ORIFICE OF AN AIR INLET PASSAGE THAT ALLOWS AIR INTO THE COMBUSTION CHAMBER OF A RAMJET 有权
标题翻译：关闭系统，用于一个排水管，特别是一个空气入口通道的通风，允许空气进入一个RAMJET的燃烧室
公开(公告)号：US20040050062A1
公开(公告)日：2004-03-18
申请号：US10041670
申请日：2002-01-10
发明人： Laurent Carton
IPC分类号： F02K007/10
CPC分类号： F02K7/18 , Y02T50/67 , Y02T50/672
摘要： Shut-off system for an orifice of a duct, particularly for an orifice of an air inlet passage that allows air into the combustion chamber of a ramjet. The shut-off system (16) comprises a shutter (15) shutting off the orifice (8) of the duct (7), and a controllable actuating device (17) capable of acting on the shutter (15) to uncover the orifice (8). The shutter (15) comprises a removable cap (18) which is held on said duct (7) and a locking device (19) which keeps the cap (18) on the duct (7) by at least one locked jaw, which is unlockable, and the actuating device (17) comprises at least one controllable striker means which is capable of unlocking the jaw in such a way as to cause the cap (18) to be ejected from the duct (7) and to uncover the orifice (8).
摘要翻译：用于管道孔口的关闭系统，特别是用于允许空气进入冲压喷气式燃烧室的空气入口通道的孔口。该关闭系统（16）包括一个切断管道（7）的孔口（8）的闸门（15）和一个能够作用在挡板（15）上以露出孔口的可控驱动装置（17） 8）。挡板（15）包括被保持在所述管道（7）上的可拆卸盖（18）和锁定装置（19），所述锁定装置（19）通过至少一个锁定的夹爪将盖（18）保持在管道（7）上，并且致动装置（17）包括至少一个可控撞击装置，其能够以使得帽（18）从管道（7）喷出并且露出孔口的方式解锁夹爪 8）。

8. 发明申请

US20040011045A1 RAMJET FOR A SUPERSONIC AND HYPERSONIC AIRCRAFT 有权
标题翻译：超级和超人飞机的RAMJET
公开(公告)号：US20040011045A1
公开(公告)日：2004-01-22
申请号：US10208752
申请日：2002-08-01
发明人： Marc Bouchez , Francois Falempin , Vadim Levine
IPC分类号： F02K007/10
CPC分类号： F02K7/10 , F02C7/042 , F02K1/08
摘要： According to the invention, the wall (5) is mounted movably as one so as to be able to slide longitudinally in translation, bringing the joint line (14) closer to the fuel injector (9) so as progressively to modify the geometries of the oxidant inlet (16) and of the combustion chamber (15), said geometries passing progressively from a first state (I) in which, for a Mach number lying between 1.5 and 3, said oxidant inlet (16) constricts said oxidant flow only slightly and the combustion chamber (15) is long and divergent, to a second state (III) in which, for a Mach number lying between 8 and 12, said oxidant inlet (16) strongly constricts said oxidant flow and said combustion chamber (15) is shorter and exhibits a constant cross section.
摘要翻译：根据本发明，壁（5）可移动地安装成能够平移地纵向滑动，使得接合线（14）更靠近燃料喷射器（9），以便逐渐改变氧化剂入口（16）和燃烧室（15），所述几何形状从第一状态（I）逐渐通过，其中对于马赫数在1.5和3之间的所述氧化剂入口（16）仅限制所述氧化剂流动并且所述燃烧室（15）长并且发散到第二状态（III），其中对于马赫数在8和12之间的所述氧化剂入口（16）强制地限制所述氧化剂流和所述燃烧室（15）较短且呈现恒定的横截面。

9. 发明申请

US20030014960A1 Impulse turbine for rotary ramjet engine 审中-公开
标题翻译：旋转式冲压发动机的脉冲涡轮
公开(公告)号：US20030014960A1
公开(公告)日：2003-01-23
申请号：US09912172
申请日：2001-07-23
申请人： RAMGEN POWER SYSTEMS, INC.
发明人： Shawn P. Lawlor
IPC分类号： F02K007/10
CPC分类号： F01D1/026 , F01D1/26
摘要： A rotary ramjet engine generator set with impulse turbine. A rotary ramjet engine is provided operating with a very low axial flow component. The engine has a closely housed rotor and shaft mounted for rotary motion with respect to an engine case. An impulse turbine is mechanically coupled on a common shaft with a rotary ramjet engine. By properly setting the turbine rotating speed with respect to ramjet rotor rotating speed, the kinetic energy of the exhaust gas from the ramjet engine is efficiently captured by the turbine. In one embodiment, the turbine is mechanically coupled, via a planetary gear set, to the output shaft of the rotary ramjet engine. The impulse turbine includes a disc to which turbine blades are affixed, and an annular housing which connects the annular disc with a central body having a circular ring gear on the inside wall thereof. The ring gear meshingly engages a plurality of planetary gears, each of which are fixed with respect to the engine casing of the rotary ramjet engine. The planetary gears reverse the direction of rotation and thus redirect power received from the ring gear to a sun gear affixed to, or splined on, or provided integrally with, an output shaft of the rotary ramjet engine. By selection of an appropriate gear ratio, the relatively slower rotating impulse turbine has its rotational energy transferred to the output shaft at the design output shaft rate of rotation.
摘要翻译：带脉冲涡轮的旋转冲压发动机发电机组。提供旋转冲压喷气发动机，其操作具有非常低的轴向流动分量。发动机具有紧密安置的转子和轴，其相对于发动机壳体进行旋转运动。冲击式涡轮机与旋转式冲压式发动机机械地联接在公共轴上。通过适当地设定相对于冲压式转子转速的涡轮机转速，来自冲压式喷气发动机的废气的动能被涡轮机有效地捕获。在一个实施例中，涡轮通过行星齿轮组机械联接到旋转冲压喷气发动机的输出轴。冲击式涡轮机包括固定有涡轮机叶片的盘，以及环形壳体，其将环形盘与在其内壁上具有圆环形齿轮的中心体连接。齿圈与多个行星齿轮啮合地啮合，每个行星齿轮相对于旋转冲压喷气发动机的发动机壳体固定。行星齿轮反转旋转方向，从而将从齿圈接收的功率转向固定到旋转式冲压式喷气发动机的输出轴上或与其成一体或与之一体地设置的太阳齿轮。通过选择适当的传动比，相对较慢的旋转冲击式涡轮机的旋转能量以设计输出轴的旋转速度传递到输出轴。

10. 发明申请

US20020023428A1 Blanking-cap system for an orifice of a conduit, in particular for an orifice of an air-intake duct into the combustion chamber of a ramjet 有权
标题翻译：用于导管孔口的封盖系统，特别是用于进入冲压式喷气发动机的燃烧室的进气管的孔口
公开(公告)号：US20020023428A1
公开(公告)日：2002-02-28
申请号：US09924457
申请日：2001-08-09
发明人： Jean-Paul Demay , Laurent Carton
IPC分类号： F02K007/10
CPC分类号： F02K9/978 , F02K7/18 , Y10T137/0536
摘要： The blanking-cap system (16) includes a glass blanking cap (15) and a destruction device (17) which comprises a projectile (18) capable of destroying the blanking cap (15), and a controllable projection means (19), which is capable of projecting the said projectile (18) and which is arranged outside the conduit (7) while being oriented in such a way as to be able to project the said projectile (18) onto the said blanking cap (15).
摘要翻译：消隐帽系统（16）包括玻璃封盖（15）和破坏装置（17），其包括能够破坏封盖（15）的射弹（18）和可控投影装置（19），其中能够突出所述抛射体（18），并且其布置在导管（7）的外部，同时被定向成使得能够将所述射弹（18）投射到所述消隐盖（15）上。

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