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    PROPULSION MODULE
    2.
    发明申请
    PROPULSION MODULE 有权
    推进模块

    公开(公告)号：US20030029162A1

    公开(公告)日：2003-02-13

    申请号：US09759933

    申请日：2001-01-12

    发明人： Von David Baker

    IPC分类号： F02K007/02

    CPC分类号： B64D27/20 ,  B64D33/02 ,  B64G1/002 ,  B64G1/401 ,  F02C7/042 ,  F02K7/04 ,  F02K7/06 ,  F02K7/20 ,  F02K9/74 ,  F02K9/78 ,  Y10T137/0536

    摘要： A propulsion module including a wave rotor detonation engine having a rotor with a plurality of fluid flow channels. The fluid flow channels extend between an inlet rotor plate, which has a pair of fixed inlet ports, and an outlet rotor plate, which has a pair of fixed outlet ports. The propulsion module includes a pair of inlet ducts have a stowed mode and a deployed mode. The pair of inlet ducts include a fluid flow passageway adapted to convey air to the pair of inlet ports. A fueling system is positioned prior to the inlet ports to deliver fuel into the air introduced through the pair of inlet ducts and into the pair of inlet ports. A pair of ignition chambers are disposed adjacent to the inlet rotor plate.

    摘要翻译： 一种推进模块，其包括具有多个流体流动通道的转子的波浪转子爆震发动机。 流体流动通道在具有一对固定入口的入口转子板和具有一对固定出口的出口转子板之间延伸。 推进模块包括一对具有收起模式和展开模式的入口管道。 一对入口管道包括适于将空气输送到一对入口端口的流体流动通道。 加油系统位于入口之前，以将燃料输送到通过一对入口管引入的空气中，并进入一对入口。 一对点火室与入口转子板相邻设置。

    Solid fuel afterburner and method of using the same to improve thrust and starting capabilities of a turbojet engine
    3.
    发明授权
    Solid fuel afterburner and method of using the same to improve thrust and starting capabilities of a turbojet engine 有权
    固体燃料加力燃烧器及其使用方法来改善涡轮喷气发动机的推力和起动能力

    公开(公告)号：US06370861B1

    公开(公告)日：2002-04-16

    申请号：US09612161

    申请日：2000-07-07

    申请人： John William Box

    发明人： John William Box

    IPC分类号： F02C1310

    CPC分类号： F02K3/10 ,  F02C7/26 ,  F02K9/08 ,  F02K9/74

    摘要： A turbojet engine includes a housing having a forward inlet nozzle, an aft exhaust nozzle, a combustion chamber therebetween, a compressor between the inlet nozzle and the combustion chamber, and a turbine between the combustion chamber and the exhaust nozzle. A liquid fuel injector is provided to inject atomized or vaporized fuel into the chamber for combustion therein. In addition, a solid fuel is provided in the aft exhaust nozzle. The solid fuel may be used to assist the starting of the engine, particularly useful under adverse starting conditions. That is, when the compressor begins to spin up to pump air through the engine, the solid fuel in the exhaust nozzle is ignited by an igniter which begins to combust with the oxygen rich air introduced by the compressor. This combustion increases the temperature in the entire engine, such that when liquid fuel is injected in the combustion chamber, the temperature is sufficiently high to allow the liquid fuel to burn in a self-sustaining manner. Thus, the engine is ignited from the back, and after ignition, the solid fuel continues to burn providing an afterburner effect boosting the thrust until the solid fuel is depleted. Alternatively, the solid fuel can be ignited after the liquid fuel is undergoing a self-sustained burn to provide an afterburner effect.

    摘要翻译： 涡轮喷气发动机包括具有正向入口喷嘴，后排气喷嘴，其间的燃烧室，入口喷嘴和燃烧室之间的压缩机以及燃烧室和排气喷嘴之间的涡轮机的壳体。 提供液体燃料喷射器以将雾化的或蒸发的燃料喷射到室中以在其中燃烧。 此外，在后排气喷嘴中设置固体燃料。 可以使用固体燃料来辅助发动机起动，在不利的起动条件下特别有用。 也就是说，当压缩机开始旋转以泵送空气通过发动机时，排气喷嘴中的固体燃料被开始与由压缩机引入的富氧空气燃烧的点火器点燃。 这种燃烧增加了整个发动机的温度，使得当液体燃料被喷射到燃烧室中时，温度足够高以允许液体燃料以自维持的方式燃烧。 因此，发动机从后部点燃，并且在点燃之后，固体燃料继续燃烧，提供加力作用，促进推力直到固体燃料耗尽。 或者，固体燃料可以在液体燃料经历自身持续燃烧之后被点燃以提供加力燃烧效应。

    HYBRID PLASMA FUEL ENGINE ROCKET
    4.
    发明申请
    HYBRID PLASMA FUEL ENGINE ROCKET 审中-公开
    混合等离子燃料发动机火箭

    公开(公告)号：US20090229240A1

    公开(公告)日：2009-09-17

    申请号：US12047303

    申请日：2008-03-12

    申请人： Keith D. Goodfellow

    发明人： Keith D. Goodfellow

    IPC分类号： F03H1/00

    CPC分类号： F03H1/0081 ,  B64G1/401 ,  B64G1/405 ,  B64G1/406 ,  F02K9/74

    摘要： A hybrid propulsion system for aerospace and other applications is disclosed in which a thruster is operable to release energy from a propellant, thereby producing an exhaust gas. The thruster is selectable from one of a plurality of thrusters that are different from one another. A plasma fuel engine (PFE) accelerator, which is coupled to the thruster in a tandem arrangement, provides partial ionization of the exhaust gas, an electric field, and a magnetic field. The electric field is aligned to accelerate the partially ionized exhaust gas and the magnetic field is aligned transversely to the electric field. The combination of the electric field and the magnetic field augment the specific impulse of the hybrid propulsion system.

    摘要翻译： 公开了一种用于航空航天和其他应用的混合推进系统，其中推进器可操作以从推进剂释放能量，从而产生废气。 推进器可以从彼此不同的多个推进器中的一个推进器中选择。 等离子体燃料发动机（PFE）加速器以串联方式联接到推进器，提供了排气，电场和磁场的部分电离。 对准电场以加速部分电离的废气，并且磁场横向于电场排列。 电场和磁场的组合增加了混合动力推进系统的比冲量。

    Jet engine using exhaust gas
    7.
    发明授权
    Jet engine using exhaust gas 有权
    喷气发动机使用废气

    公开(公告)号：US07021043B2

    公开(公告)日：2006-04-04

    申请号：US10758928

    申请日：2004-01-16

    申请人： Jae-Chang Lee

    发明人： Jae-Chang Lee

    IPC分类号： F02K3/02

    CPC分类号： F02K7/16 ,  F01D5/142 ,  F02K3/062 ,  F02K9/74

    摘要： A jet engine using exhaust gas to get the propulsive force by rotating a fan within the exhaust gas burned in and emitted from the engine includes a body, a burner installed to the body to inject and burn the fuel in compressed air, a high-pressure turbine for giving rotational force by high-pressure exhaust gas from the burner, a low-pressure turbine for giving rotational force by low-pressure exhaust from the high-pressure turbine, a rotary shaft combined to a rotational center of the high-pressure and low-pressure turbines, and a propulsive force providing unit which is rotating together with the rotary shaft to change component of lateral velocity of the exhaust gas emitted through the turbines from the burner to be directed rearward.

    摘要翻译： 使用废气通过使从发动机燃烧并从发动机排出的废气中旋转风扇来获得推进力的喷气发动机包括主体，安装在主体上以在压缩空气中喷射和燃烧燃料的燃烧器，高压 用于通过来自燃烧器的高压废气产生旋转力的涡轮机，用于通过来自高压涡轮机的低压排气产生旋转力的低压涡轮机，组合到高压涡轮的旋转中心的旋转轴和 低压涡轮机以及与旋转轴一起旋转的推进力提供单元，以将通过涡轮机排出的废气的侧向速度的分量从燃烧器改变为向后。

    Propulsion module
    8.
    发明授权
    Propulsion module 有权
    推进模块

    公开(公告)号：US06584764B2

    公开(公告)日：2003-07-01

    申请号：US09759933

    申请日：2001-01-12

    申请人： Von David Baker

    发明人： Von David Baker

    IPC分类号： F02K702

    CPC分类号： B64D27/20 ,  B64D33/02 ,  B64G1/002 ,  B64G1/401 ,  F02C7/042 ,  F02K7/04 ,  F02K7/06 ,  F02K7/20 ,  F02K9/74 ,  F02K9/78 ,  Y10T137/0536

    摘要： A propulsion module including a wave rotor detonation engine having a rotor with a plurality of fluid flow channels. The fluid flow channels extend between an inlet rotor plate, which has a pair of fixed inlet ports, and an outlet rotor plate, which has a pair of fixed outlet ports. The propulsion module includes a pair of inlet ducts have a stowed mode and a deployed mode. The pair of inlet ducts include a fluid flow passageway adapted to convey air to the pair of inlet ports. A fueling system is positioned prior to the inlet ports to deliver fuel into the air introduced through the pair of inlet ducts and into the pair of inlet ports. A pair of ignition chambers are disposed adjacent to the inlet rotor plate.

    摘要翻译： 一种推进模块，其包括具有多个流体流动通道的转子的波浪转子爆震发动机。 流体流动通道在具有一对固定入口的入口转子板和具有一对固定出口的出口转子板之间延伸。 推进模块包括一对具有收起模式和展开模式的入口管道。 一对入口管道包括适于将空气输送到一对入口端口的流体流动通道。 加油系统位于入口之前，以将燃料输送到通过一对入口管引入的空气中，并进入一对入口。 一对点火室与入口转子板相邻设置。

    Hybrid chemical/electromagnetic propulsion system
    9.
    发明授权
    Hybrid chemical/electromagnetic propulsion system 失效
    混合化学/电磁推进系统

    公开(公告)号：US5170623A

    公开(公告)日：1992-12-15

    申请号：US646309

    申请日：1991-01-28

    申请人： Charles L. Dailey ,  Ralph H. Lovberg ,  Robert L. Sackheim ,  John J. Biess

    发明人： Charles L. Dailey ,  Ralph H. Lovberg ,  Robert L. Sackheim ,  John J. Biess

    IPC分类号： F02K9/74 ,  F02K9/97 ,  F02K99/00 ,  F03H1/00 ,  H02K44/00

    CPC分类号： F03H1/0081 ,  F02K9/74 ,  F02K9/97 ,  H02K44/00

    摘要： A hybrid chemical/electromagnetic propulsion system which combines thermal expansion of a chemically-reacted propellant with electromagnetic acceleration of the propellant to provide an efficient propulsion system that operates in the specific impulse I.sub.sp range of 800 to 2500 seconds. The hybrid chemical/electromagnetic propulsion system includes a reaction chamber, an expansion nozzle mounted to the exit of the reaction chamber, and an induction coil wound around a portion of the expansion nozzle. The reaction chamber supports the combustion or chemical reaction of a propellant to form high-temperature ionizable reaction products. The expansion nozzle then expands these high-temperature reaction products to generate thrust. The induction coil generates a varying electric and magnetic field which ionizes and magnetically accelerates the reaction products to generate additional thrust. A drive circuit supplies current to the induction coil in a manner that maximizes this additional thrust.

    摘要翻译： 一种混合化学/电磁推进系统，其将化学反应的推进剂的热膨胀与推进剂的电磁加速相结合，以提供在800至2500秒的比脉冲Isp范围内操作的有效的推进系统。 混合型化学/电磁推进系统包括反应室，安装在反应室出口处的膨胀喷嘴和缠绕在膨胀喷嘴的一部分上的感应线圈。 反应室支持推进剂的燃烧或化学反应，形成高温可电离的反应产物。 膨胀喷嘴然后膨胀这些高温反应产物以产生推力。 感应线圈产生变化的电场和磁场，其电离并磁加速反应产物以产生额外的推力。 驱动电路以使该附加推力最大化的方式向感应线圈提供电流。