公开(公告)号：US06516605B1

公开(公告)日：2003-02-11

申请号：US09882649

申请日：2001-06-15

申请人： Gregory Vincent Meholic

发明人： Gregory Vincent Meholic

IPC分类号： F02K7075

CPC分类号： F02K9/97 ,  F02K7/075 ,  F05D2240/1281

摘要： An aerospike engine has at least one nozzle surface and a plurality of pulse detonation devices mounted to the nozzle surface in place of the more common deflagration-based combustors. Each pulse detonation device is oriented such that its combustion products are directed along the nozzle surface Incorporating pulse detonation devices into the aerospike engine produces the advantage of a more efficient thermodynamic cycle. The pulse detonation aerospike engine is also capable of operating on either air or oxidizer.

摘要翻译： Aerospike发动机具有至少一个喷嘴表面和多个安装到喷嘴表面的脉冲爆震装置，代替更常见的基于爆燃的燃烧器。 每个脉冲爆震装置被定向成使得其燃烧产物沿着喷嘴表面引导将脉冲爆震装置引入到空气喷射发动机中产生更有效的热力循环的优点。 脉冲爆震Aerospike发动机也能够在空气或氧化剂上操作。

公开(公告)号：US06477829B1

公开(公告)日：2002-11-12

申请号：US09567374

申请日：2000-05-09

申请人： Louis G. Hunter ,  Billy D. Couch ,  Paul E. Hagseth

发明人： Louis G. Hunter ,  Billy D. Couch ,  Paul E. Hagseth

IPC分类号： F02K311

CPC分类号： F02K7/075 ,  F02K3/00 ,  F05D2260/40 ,  F05D2260/4023 ,  F05D2270/13

摘要： A combined cycle pulse combustion/gas turbine engine has a gas turbine engine used in conjunction with a plurality of pulse combustion engines. In one embodiment, the gas turbine engine includes a housing, a bypass fan, a central engine core, and a diffuser section. The diffuser section is used to route bypass air from the bypass fan around the central engine core and out of the housing. The pulse engines are mounted in the diffuser section and receive bypass air from the bypass fan. In a first alternate embodiment, bypass air is routed from the diffuser section through a duct to the pulse engine. A valve is disposed between the bypass fan and the pulse engines for selectively allowing bypass air from the bypass fan to enter the duct. In a second alternate embodiment, a fan mounts to each inlet port. The gas turbine engine has a drive shaft that drives the fan. A clutch selectively disengages the fans.

摘要翻译： 联合循环脉冲燃烧/燃气涡轮发动机具有与多个脉冲燃烧发动机结合使用的燃气涡轮发动机。 在一个实施例中，燃气涡轮发动机包括壳体，旁通风扇，中心发动机芯和扩散器部分。 扩散器部分用于将旁路风扇的旁路空气绕过中心发动机芯并将其从壳体中排出。 脉冲发动机安装在扩散器部分，并从旁路风扇接收旁路空气。 在第一替代实施例中，旁路空气从扩散器段通过导管路由到脉冲发动机。 旁通风扇和脉冲发动机之间设置有阀，用于选择性地允许来自旁路风扇的旁路空气进入管道。 在第二替代实施例中，风扇安装到每个入口端口。 燃气涡轮发动机具有驱动风扇的驱动轴。 离合器选择性地使风扇脱离。

公开(公告)号：US5901550A

公开(公告)日：1999-05-11

申请号：US618001

申请日：1996-03-18

申请人： Thomas R. A. Bussing ,  Thomas E. Bratkovich

发明人： Thomas R. A. Bussing ,  Thomas E. Bratkovich

IPC分类号： B01J3/08 ,  B05B7/00 ,  C23C4/12 ,  F01D5/28 ,  F02K7/06 ,  F02K7/075 ,  F02K9/97 ,  F02C5/02

CPC分类号： F02K9/974 ,  B01J3/08 ,  B05B7/0006 ,  C23C4/126 ,  F01D5/288 ,  F02K7/06 ,  F02K7/075 ,  F02K9/972

摘要： The invention provides a liquid fueled pulsed detonation air breathing engine. The engine has at least one, and preferably a multiplicity of, detonation chambers, each of which has an inlet end for opening and receiving a charge of fuel and air, and an outlet end for discharging combustion product gases. A fast-acting valve is located above the inlet ends of the detonation chambers and cyclically opens the fuel and air receiving openings in the inlet ends of the detonation chambers to allow a fuel/air charge to enter the chambers. In a preferred embodiment, the valve is of a rotary type with a body that has at least one opening through which fuel and air can flow into the inlet end of the detonation chamber. Once the valve has closed, detonation is initiated by an ignitor and impulse force is provided by the resultant shock wave. Thereafter, the valve opens again so that the detonation chamber can be charged with fuel and air to recommence the cycle. The invention also provides an embodiment of an engine that has both inlet and outlet valves. These valves operate out of phase so that when the inlet valve is open to receive fuel and air into the detonation chamber, the outlet valve is closed. When detonation commences, the outlet valve is open and the inlet valve is closed. Optionally, a source of oxygen allows a stratified charge in the engine to enhance detonation. Also provided is a control system (48) for sensing the position of the valves, (58, 80) and using this sensed position to inject fuel, inject oxygen and ignite the fuel and air mixture.

摘要翻译： 本发明提供一种液体燃料脉冲爆震空气呼吸发动机。 发动机具有至少一个，优选地是多个爆轰室，每个都具有用于打开和接收燃料和空气的进料口的入口端，以及用于排出燃烧产物气体的出口端。 快速作用阀位于引爆室的入口端上方，并循环地打开引爆室入口端的燃料和空气接收孔，以允许燃料/空气进入腔室。 在优选实施例中，阀是具有主体的旋转型，其具有至少一个开口，燃料和空气可以通过该开口流入爆炸室的入口端。 一旦阀门关闭，爆震就由点火器启动，冲击力由所产生的冲击波提供。 此后，阀再次打开，使得引爆室可以充入燃料和空气以重新开始循环。 本发明还提供了具有入口和出口阀的发动机的实施例。 这些阀门异相工作，因此当入口阀打开以接收燃料和空气进入爆轰室时，出口阀关闭。 当爆炸开始时，出口阀打开，进气阀关闭。 可选地，氧源允许发动机中的分层装料增强爆震。 还提供了一种用于感测阀（58,80）的位置并使用该感测位置喷射燃料，注入氧气并点燃燃料和空气混合物的控制系统（48）。

公开(公告)号：US5419118A

公开(公告)日：1995-05-30

申请号：US183726

申请日：1994-01-19

申请人： Hugh J. McSpadden ,  Donald E. Olander

发明人： Hugh J. McSpadden ,  Donald E. Olander

IPC分类号： F02K7/075 ,  F02K9/26 ,  F02K9/30 ,  F02K9/28

CPC分类号： F02K7/075 ,  F02K9/26 ,  F02K9/30

摘要： A motor for impelling a missile or projectile has a housing and a plurality of spaced walls defining progressive compartments in the housing. A nozzle in one of the compartments produces a thrust for the missile or projectile when pressurized gases flow through it. Igniters extending into the individual compartments ignite propellants in such compartments. The igniter in an individual one of the compartments is energized initially and the igniters progressively displaced from such individual compartment are thereafter energized sequentially. Each wall separating an individual pair of adjacent compartments has a normally closed valve. Each valve has a first orifice of relatively great area in the compartment closer to the nozzle and a second orifice of limited area in the compartment further from the nozzle. A membrane between the orifices prevents the valve from being opened by a pressure from the closer compartment until this pressure becomes relatively great (e.g. 6500 psi). When a comparatively low pressure (e.g. 1500 psi) is applied in the second orifice by propellant combusting in the further compartment, the membrane ruptures. The rupture is facilitated by dimpling the membrane in the direction from the second orifice toward the first orifice. When the membrane is ruptured, gases from the propellant combusting in the further compartment flow through the valve and then through the nozzle and gradually erode the membrane and orifice. This causes the gases in the compartments to be maintained at equal pressures sufficiently great to sustain the propellant combustion in the further compartment.

摘要翻译： 用于推动导弹或射弹的电动机具有壳体和多个隔开的壁，其在壳体中限定渐进的隔室。 其中一个隔间内的喷嘴在加压气体流经时会产生导弹或弹丸的推力。 延伸到各个隔间的点火器在这样的隔间中点燃推进剂。 单个隔室中的点火器最初被激发，然后逐渐地从这样的单独隔室逐渐移位的点火器依次通电。 分离一对相邻隔室的每个壁具有常闭阀。 每个阀具有在更靠近喷嘴的隔室中具有相对较大面积的第一孔口，以及隔室中距离喷嘴更有限的区域的第二孔口。 孔之间的膜防止阀从较近隔室的压力打开，直到该压力变得相对较大（例如6500psi）为止。 当通过在另外的隔室中燃烧的推进剂在第二孔中施加比较低的压力（例如1500psi）时，膜破裂。 通过使膜沿着从第二孔口朝向第一孔口的方向变暗来促进破裂。 当膜破裂时，来自在另外的室中燃烧的推进剂的气体流过阀，然后通过喷嘴并逐渐侵蚀膜和孔。 这导致隔室中的气体保持足够大的相等的压力，以维持在另外的隔室中的推进剂燃烧。

公开(公告)号：US4674951A

公开(公告)日：1987-06-23

申请号：US770247

申请日：1985-08-28

申请人： Gerard E. A. Jourdain ,  Marcel R. Soligny

发明人： Gerard E. A. Jourdain ,  Marcel R. Soligny

IPC分类号： F04D27/02

CPC分类号： F02K7/075 ,  F04D27/0215 ,  F04D27/023 ,  Y02T50/672

摘要： A ring of an annular valve assembly is movable in the direction of its longitudinal axis and is intended for an axial compressor blow-off arrangement. The ring takes the form of an axially orientated channel-section member having a first annular skin of concave section nested in a second annular skin also of concave section. A cavity filled with a synthetic resin filler is defined by the two skins. The blow-off arrangement for an axial-flow compressor of a turbo-jet engine, which incorporates this ring, comprises an annular opening with which the ring cooperates to re-form the wall of the air flow when the blow-off arrangement is inoperative.

摘要翻译： 环形阀组件的环可以在其纵向轴线的方向上移动，并且用于轴向压缩机吹出装置。 该环采取轴向定向的通道截面构件的形式，其具有嵌在第二环形表皮中的凹部的第一环形表皮，也是凹形部分。 填充有合成树脂填料的空腔由两个表皮限定。 涡轮喷气发动机的轴流式压缩机的排放装置，其结合了该环，包括环形开口，当排放装置不起作用时，该环与该空气合流以重新形成空气流的壁 。

公开(公告)号：US3824787A

公开(公告)日：1974-07-23

申请号：US29074072

申请日：1972-09-20

申请人： ETESSAM A

发明人： ETESSAM A

IPC分类号： F02K7/075 ,  F02K7/04

CPC分类号： F02K7/075

摘要： A gas generator for a turbine or jet power plant comprising a pair of coextensive combustion chambers normally coaxially arranged between the inlet and outlet and each operating on the pulse jet principle, the combustion chambers converging towards the outlet in the form of mutually inductive nozzles so that the combustion chambers operate in an alternate cycle providing continuous throughput of air from inlet to outlet. Embodiments include power plants incorporating the combustion chambers and suitable for stationary purposes such as road vehicles, subsonic aircraft and supersonic aircraft, turbine and bypass engines.

摘要翻译： 一种用于涡轮或喷气动力装置的气体发生器，包括一对共同延伸的燃烧室，通常同轴地布置在入口和出口之间，并且各自以脉冲喷射原理运行，燃烧室以相互感应的喷嘴的形式会聚到出口，使得 燃烧室以交替的循环运行，从而从进口到出口连续提供空气的产量。 实施例包括结合有燃烧室并适用于固定目的的发电厂，例如道路车辆，亚音速飞机和超音速飞机，涡轮机和旁路引擎。

公开(公告)号：US2705396A

公开(公告)日：1955-04-05

申请号：US33763453

申请日：1953-02-18

申请人： BOYCE ARTHUR L ,  GEORGE COY L

发明人： BOYCE ARTHUR L ,  GEORGE COY L

IPC分类号： F02K7/075

CPC分类号： F02K7/075