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公开(公告)号：US3111956A
公开(公告)日：1963-11-26
申请号：US19653962
申请日：1962-03-15
CPC分类号： F02K9/58 , F02K9/74 , Y10T137/1774 , Y10T137/86847
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公开(公告)号：US06964154B1
公开(公告)日：2005-11-15
申请号：US10390253
申请日：2003-03-11
CPC分类号： F02K9/80 , F02K9/56 , F02K9/766 , F02K9/805 , F02K9/97 , F05D2240/1281 , F05D2240/40
摘要： A rocket engine assembly is provided for a vertically launched rocket vehicle. A rocket engine housing of the assembly includes two or more combustion chambers each including an outlet end defining a sonic throat area. A propellant supply for the combustion chambers includes a throttling injector, associated with each of the combustion chambers and located opposite to sonic throat area, which injects the propellant into the associated combustion chamber. A modulator, which may form part of the injector, and which is controlled by a controller, modulates the flow rate of the propellant to the combustion chambers so that the chambers provide a vectorable net thrust. An expansion nozzle or body located downstream of the throat area provides expansion of the combustion gases produced by the combustion chambers so as to increase the net thrust.
摘要翻译： 为垂直发射的火箭车提供火箭发动机总成。 组件的火箭发动机壳体包括两个或更多个燃烧室，每个燃烧室包括限定声音喉部区域的出口端。 用于燃烧室的推进剂供应包括与每个燃烧室相关并且与声音喉部区域相对定位的节流喷射器，其将推进剂喷射到相关联的燃烧室中。 可以形成喷射器的一部分并且由控制器控制的调制器调节推进剂到燃烧室的流速，使得腔室提供可向量的净推力。 位于喉部区域下游的膨胀喷嘴或本体提供由燃烧室产生的燃烧气体的膨胀，以增加净推力。
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公开(公告)号：US5170623A
公开(公告)日：1992-12-15
申请号：US646309
申请日：1991-01-28
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。
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公开(公告)号：US20050178104A1
公开(公告)日：2005-08-18
申请号：US11095646
申请日：2005-03-31
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.
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公开(公告)号：US2422744A
公开(公告)日：1947-06-24
申请号：US55655844
申请日：1944-09-30
申请人： GEN TIRE & RUBBER CO
发明人： O'NEIL WILLIAM F
CPC分类号： F02K9/74 , B64D27/023 , Y10S100/911
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公开(公告)号：US12006068B2
公开(公告)日：2024-06-11
申请号：US17580727
申请日：2022-01-21
发明人： Weiming Ma , Yuxing Zhang , Mingyuan Zhang , Xiangming Zhang , Weichao Li , Xinlin Long , Chen Deng
CPC分类号： B64G1/002 , H02N11/006 , B60L50/13 , F02K9/74
摘要： A space launch system and method through electromagnetic pushing. The space launch system comprises an energy storage subsystem, an energy conversion subsystem, a linear motor subsystem, and a control maintenance subsystem. The space launch system converts the electric energy into an electromagnetic force. Through the electromagnetic force, a rocket is pushed to be accelerated to a certain speed along an electromagnetic launching track to realize the launching of the rocket.
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公开(公告)号：US11846251B1
公开(公告)日：2023-12-19
申请号：US16857609
申请日：2020-04-24
CPC分类号： F02K7/18 , F02K9/48 , F02K9/64 , F02K9/74 , F05D2220/80 , F05D2240/35 , F05D2260/205
摘要： The inventors introduce the Borissov-Markusic Cycle as the new rocket engine cycle to solve the problem of low efficient open gas generator or tap-off gas generator cycles used to supply power to turbopump. A liquid rocket engine directs turbopump exhaust from a turbopump to a booster engine having an intake to accept ambient airflow, such as a variation of a ramjet, scramjet or dual mode ram scramjet engine. The turbopump is powered by combustion gases, such as from a gas generator or a tap-off manifold interfaced with the liquid rocket engine combustion chamber, and applies energy of the combustion gases to pump fuel and/or liquid oxygen to the liquid rocket engine combustion chamber. The combustion gases have a fuel-rich composition that includes unconsumed fuel from incomplete oxidation so that, upon injection into the combustion chamber of the booster engine, oxidation by ambient air of the unconsumed fuel releases energy to generate thrust with the booster engine.
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公开(公告)号：US20120198814A1
公开(公告)日：2012-08-09
申请号：US13502373
申请日：2010-10-18
申请人： Israel Hirshberg
发明人： Israel Hirshberg
CPC分类号： F01N5/02 , F02K5/02 , F05D2220/76 , Y02T10/16
摘要： A method of increasing internal combustion engine efficiency is based on using engine cooling air and exhaust gas by flowing this mixture into a convergent nozzle thus accelerating the gas mixture and eject it through nozzle exit, thus generating thrust in a desired direction which could push a land air or sea vehicle. Another option is to use the accelerated gas to drive a turbine that could add its torque to the engine or to drive electrical generator that produces electricity.
摘要翻译： 提高内燃机效率的方法是基于通过将该混合物流入会聚喷嘴来使用发动机冷却空气和废气，从而加速气体混合物并将其通过喷嘴出口喷射，从而沿着期望的方向产生推力，这可以推动陆地 空中或海上车辆 另一种选择是使用加速气体来驱动涡轮机，该涡轮机可以将其扭矩增加到发动机或驱动产生电力的发电机。
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公开(公告)号：US07107755B2
公开(公告)日：2006-09-19
申请号：US10207796
申请日：2002-07-31
申请人： Karim El Hamel , Arnold C Newton
发明人： Karim El Hamel , Arnold C Newton
CPC分类号： B64C11/001 , B64C39/10 , B64C2039/105 , B64D27/10 , B64D27/12 , B64D27/14
摘要： An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit in a position spaced from the body or airframe of the aircraft.
摘要翻译： 发动机装置（14）包括燃气涡轮发动机单元（16），并且第一和第二支撑构件（18,20）从发动机壳体（22）的结构部件（24）延伸，以将发动机单元支撑在间隔开的位置 从飞机的身体或机身。
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