公开(公告)号：US20050279083A1

公开(公告)日：2005-12-22

申请号：US10870877

申请日：2004-06-18

申请人： Keith McManus ,  Anthony Dean ,  Venkat Tangirala

发明人： Keith McManus ,  Anthony Dean ,  Venkat Tangirala

IPC分类号： F02K7/02

CPC分类号： F02K7/04 ,  F23C15/00 ,  F23L7/007 ,  F23R7/00 ,  Y02E20/344

摘要： In the present invention, at least one detonation initiator is positioned downstream of a main combustion chamber, with the initiator oriented such that it projects a detonation initiation wave forward into the main combustion chamber. The main combustion chamber contains a wave reflection surface. The detonation initiation wave is directed into the main combustion chamber and at the wave reflector surface and is used to initiate, or assist in the initiation of, a fuel and gas mixture in the main combustion chamber. The fuel and gas mixture is detonated, creating a high temperature and high pressure wave that is directed out of the main combustion chamber.

摘要翻译： 在本发明中，至少一个引爆引发剂位于主燃烧室的下游，其中起爆器被定向为使得爆炸起始波向前推入主燃烧室。 主燃烧室包含波反射面。 引爆起始波被引导到主燃烧室和波浪反射器表面，并用于启动或协助起动主燃烧室中的燃料和气体混合物。 燃料和气体混合物被引爆，产生高温和高压波，该高压和高压波被引导出主燃烧室。

公开(公告)号：US20050120700A1

公开(公告)日：2005-06-09

申请号：US10730219

申请日：2003-12-08

申请人： Venkat Tangirala ,  Anthony Dean ,  Ivett Leyva

发明人： Venkat Tangirala ,  Anthony Dean ,  Ivett Leyva

IPC分类号： F02K3/08 ,  F02K7/04 ,  F02K9/78 ,  F23R7/00 ,  F02K5/02

CPC分类号： F02K3/08 ,  F02K7/04 ,  F02K9/78 ,  F23R7/00

摘要： A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high pressure conditions in the resonator in order to create optimal conditions for detonation initiation. A mixture of a fuel and a gas is burned in the pre-combustor and is passed through the nozzle into the geometric resonator, where the burned mixture is detonated. The detonation propagates through the resonator exit nozzle thus generating thrust.

摘要翻译： 两级脉冲爆震系统包括预燃烧器和通过会聚发散喷嘴连接到预燃烧器的几何谐振器，以在谐振器中产生高温和高压条件，以便产生爆炸开始的最佳条件。 燃料和气体的混合物在预燃烧器中燃烧并且通过喷嘴进入几何谐振器，其中燃烧的混合物被引爆。 爆震通过谐振器出口喷嘴传播，从而产生推力。

公开(公告)号：US20070180815A1

公开(公告)日：2007-08-09

申请号：US11554897

申请日：2006-10-31

申请人： Venkat Tangirala ,  Jonathan Janssen ,  Anthony Dean

发明人： Venkat Tangirala ,  Jonathan Janssen ,  Anthony Dean

IPC分类号： F02K7/02

CPC分类号： F02K7/02

摘要： A supersonic propulsion system is provided. The supersonic propulsion system includes a plurality of systems for efficiently creating cyclic detonations and at least one rocket booster device. Each of the systems include at least a first initiator chamber configured to generate an initial wave, at least one main chamber coupled to the first initiator chamber. The main chamber is configured to generate a main wave and to output products of supersonic combustion. The products are generated within the main chamber. The main chamber is configured to enable the main wave to travel upstream and downstream within the main chamber when the first initiator chamber is located outside the main chamber. The system further includes an initial connection section located between the first initiator chamber and the main chamber that enhances a combustion process via shock focusing and shock reflection.

摘要翻译： 提供超音速推进系统。 超音速推进系统包括用于有效地产生循环爆炸的多个系统和至少一个火箭增压装置。 每个系统包括至少一个配置成产生初始波的第一启动器室，耦合到第一起动器室的至少一个主室。 主室被配置为产生主波并输出超音速燃烧的产物。 产品在主室内产生。 主室被构造成使得当第一起动器室位于主室外部时，能够使主波浪在主室内的上游和下游行进。 该系统还包括位于第一起动器室和主室之间的初始连接部分，其通过冲击聚焦和冲击反射增强燃烧过程。

公开(公告)号：US20070130830A1

公开(公告)日：2007-06-14

申请号：US11302658

申请日：2005-12-14

申请人： Balachandar Varatharajan ,  Venkat Tangirala ,  Joel Haynes ,  Anthony Dean

发明人： Balachandar Varatharajan ,  Venkat Tangirala ,  Joel Haynes ,  Anthony Dean

IPC分类号： B01J8/00

CPC分类号： B01J12/007 ,  B01J12/00 ,  B01J19/249 ,  B01J2219/0004 ,  B01J2219/2453 ,  B01J2219/2466 ,  B01J2219/247 ,  B01J2219/2479 ,  C01B3/363 ,  C01B3/386 ,  C01B2203/025 ,  C01B2203/0261 ,  C01B2203/062 ,  C01B2203/0811 ,  C01B2203/1064 ,  C01B2203/107

摘要： A multi-stage combustion fuel reformer (20) wherein heat energy from a leaner-burning stage (22) is used to accelerate the fuel reforming kinetics of a richer-burning stage (28). The two stages may be axially arranged (36) or radially arranged (50) with respect to each other. Both stages (64, 66) may utilize gas-phase combustion; or both stages (78, 82) may utilized catalytic combustion; or both gas-phase ((90) and catalytic combustion (92) may be used together. The multi-stage reformer (112) may form part of a gas-to-liquid fuel reforming system (110).

摘要翻译： 多级燃烧燃料重整器（20），其中使用来自较冷燃烧级（22）的热能来加速更加燃烧的燃料级（28）的燃料重整动力学。 两个阶段可以相对于彼此轴向地布置（36）或径向布置（50）。 两级（64,66）可以利用气相燃烧; 或两级（78,82）可以使用催化燃烧; 或者可以一起使用气相（（90）和催化燃烧（92）），多级重整器（112）可以形成气体 - 液体燃料重整系统（110）的一部分。

公开(公告)号：US20070180832A1

公开(公告)日：2007-08-09

申请号：US11346714

申请日：2006-02-03

申请人： Ross Kenyon ,  Venkat Tangirala ,  Kevin Hinckley ,  Anthony Dean ,  Stephen Myers

发明人： Ross Kenyon ,  Venkat Tangirala ,  Kevin Hinckley ,  Anthony Dean ,  Stephen Myers

IPC分类号： F02C5/00

CPC分类号： F02K7/02

摘要： A system for efficiently creating cyclic detonations is provided. The system includes at least a first initiator chamber configured to generate an initial wave, at least one main chamber coupled to the first initiator chamber. The main chamber is configured to generate a main wave and to output products of supersonic combustion. The products are generated within the main chamber. The main chamber is configured to enable the main wave to travel upstream and downstream within the main chamber when the first initiator chamber is located outside the main chamber. The system further includes an initial connection section located between the first initiator chamber and the main chamber that enhances a combustion process via shock focusing and shock reflection.

摘要翻译： 提供了一种有效地创建循环爆炸的系统。 该系统包括至少一个配置成产生初始波的第一起动器室，耦合到第一起动器室的至少一个主室。 主室被配置为产生主波并输出超音速燃烧的产物。 产品在主室内产生。 主室被构造成使得当第一起动器室位于主室外部时，能够使主波浪在主室内的上游和下游行进。 该系统还包括位于第一起动器室和主室之间的初始连接部分，其通过冲击聚焦和冲击反射增强燃烧过程。

公开(公告)号：US20070180814A1

公开(公告)日：2007-08-09

申请号：US11347464

申请日：2006-02-03

申请人： Venkat Tangirala ,  Kevin Hinckley ,  David Chapin ,  Anthony Dean

发明人： Venkat Tangirala ,  Kevin Hinckley ,  David Chapin ,  Anthony Dean

IPC分类号： F02K7/02

CPC分类号： F02K7/02

摘要： A system for generating thrust is provided. The system includes a first injector, an inner tube configured to receive fuel from the first injector via a first port of the inner tube, where at least a portion of fuel in liquid phase received by the inner tube is configured to flash vaporize upon entering the inner tube via the first port.

摘要翻译： 提供了一种用于产生推力的系统。 该系统包括第一喷射器，内管，其构造成经由内管的第一端口从第一喷射器接收燃料，其中由内管接收的液相中的至少一部分燃料被配置为在进入 内管通过第一个端口。

公开(公告)号：US20070186556A1

公开(公告)日：2007-08-16

申请号：US11352773

申请日：2006-02-13

申请人： Adam Rasheed ,  Keith McManus ,  Anthony Dean

发明人： Adam Rasheed ,  Keith McManus ,  Anthony Dean

IPC分类号： F23R7/00

CPC分类号： F23R7/00

摘要： A method for operating a pulse detonation engine, wherein the method includes channeling air flow from a pulse detonation combustor into a flow mixer having an inlet portion, an outlet portion, and a body portion extending therebetween. The method also includes channeling ambient air past the flow mixer and mixing the air flow discharged from the pulse detonation combustor with the ambient air flow such that a combined flow is generated from the flow mixer that has less flow variations than the air flow discharged from the pulse detonation combustor.

摘要翻译： 一种用于操作脉冲爆震引擎的方法，其中所述方法包括将来自脉冲爆震燃烧器的空气流引导到具有入口部分，出口部分和在其间延伸的主体部分的流动混合器。 该方法还包括将环境空气引导通过流动混合器并将从脉冲爆震燃烧器排放的空气流与环境空气流混合，使得从流动混合器产生的组合流量具有比从 脉冲爆震燃烧器。

公开(公告)号：US20070180833A1

公开(公告)日：2007-08-09

申请号：US11348869

申请日：2006-02-07

申请人： Adam Rasheed ,  Anthony Dean

发明人： Adam Rasheed ,  Anthony Dean

IPC分类号： F02C5/00

CPC分类号： F02C5/02 ,  F02C5/11

摘要： A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the chamber to facilitate controlling air flow into the chamber. The device also includes a body portion extending downstream from and circumferentially around the inlet, wherein the body portion is positioned in flow communication with the inlet.

摘要翻译： 一种用于脉冲爆震室的流量控制装置，包括与压缩空气源流动连通的入口。 入口至少部分地延伸到室中以便于控制进入室的空气流。 该装置还包括从入口的下游和周向延伸的主体部分，其中主体部分定位成与入口流动连通。

公开(公告)号：US20070180811A1

公开(公告)日：2007-08-09

申请号：US11349489

申请日：2006-02-07

申请人： Adam Rasheed ,  Anthony Dean

发明人： Adam Rasheed ,  Anthony Dean

IPC分类号： F02C5/00

CPC分类号： F23R7/00 ,  F02C5/00 ,  F02C5/10 ,  F05D2220/326 ,  F05D2220/327

摘要： A pulse detonation combustor (PDC) assembly includes an upstream chamber forming an inlet plenum, a downstream chamber including a downstream portion of at least one PDC tube, and an integrated PDC head coupled to the upstream chamber and the downstream chamber. The integrated PDC head is configured to facilitate fuel injection and ignition within the PDC tube. The PDC tube includes an inner seal surface and an outer seal surface configured to mate with the inner seal surface, wherein the inner seal surface includes an elevated section thereon that engages with the outer seal surface such that the PDC tube is free to partially pivot about a longitudinal axis thereof.

摘要翻译： 脉冲爆震燃烧器（PDC）组件包括形成入口增压室的上游室，包括至少一个PDC管的下游部分的下游室以及耦合到上游室和下游室的集成PDC头。 集成的PDC头构造成便于PDC管内的燃料喷射和点火。 PDC管包括内密封表面和构造成与内密封表面配合的外密封表面，其中内密封表面包括在其上的升高部分，其与外密封表面接合，使得PDC管能够围绕 其纵轴。

公开(公告)号：US20070137616A1

公开(公告)日：2007-06-21

申请号：US11312409

申请日：2005-12-21

申请人： Bruce Badding ,  Adam Rasheed ,  Anthony Dean

发明人： Bruce Badding ,  Adam Rasheed ,  Anthony Dean

IPC分类号： F02P5/00 ,  F02B19/00 ,  F02C7/26

CPC分类号： F02P23/04 ,  F02C5/02 ,  F02C7/264 ,  F02K1/34 ,  F05D2260/96 ,  F05D2260/962 ,  F05D2270/14

摘要： An aircraft engine is provided with at least one pulse detonation device, and the operational frequency of the pulse detonation device is varied over an operational range of frequencies around a mean frequency value. The pulse detonation device can be positioned upstream, downstream or adjacent to a turbine section of the engine. An additional embodiment of the present invention is an aircraft engine provided with more than one pulse detonation device, and the operational frequency of one, or more, of the pulse detonation devices is varied over an operational range of frequencies around a mean frequency value.

摘要翻译： 飞机发动机设置有至少一个脉冲爆震装置，并且脉冲爆震装置的工作频率在围绕平均频率值的频率的工作范围内变化。 脉冲爆震装置可以位于发动机的涡轮机部分的上游，下游或邻近。 本发明的另外的实施例是设置有多于一个脉冲爆震装置的飞机发动机，并且脉冲爆震装置中的一个或多个的操作频率在围绕平均频率值的频率的工作范围内变化。