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公开(公告)号：US10539073B2
公开(公告)日：2020-01-21
申请号：US15530910
申请日：2017-03-20
摘要： This invention performs the gas pressurization task of a centrifugal compressor gas turbine engine in a new way. In this invention gas compression takes place by using pinwheel-like thrusters to induce a very high velocity full forced vortex in the gas being compressed. Much higher “tip” velocities can be achieved because no strength-limited solid centrifugal impeller is required to spin up the gas. Due to the consequent very high vortex velocity a single stage pressure ratio of twenty five to one, or more, may be possible. Because there is no high pressure turbine, the gas pressure delivered to some downstream useful work device is much higher than is the case with conventional gas turbine engines. The invention's compressor requires no major moving parts except for the gas flow. The consequence is that the invention is predicted to have substantially better performance and general characteristics than conventional gas turbine engines.
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公开(公告)号：US20190264918A1
公开(公告)日：2019-08-29
申请号：US15904892
申请日：2018-02-26
发明人： Sibtosh Pal , Steven Clayton Vise , Arthur Wesley Johnson , Clayton Stuart Cooper , Joseph Zelina
摘要： A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. A strut is extended through the gas flowpath between the longitudinal walls. An inner wall assembly is extended from the longitudinal wall and the strut into the gas flowpath. The inner wall assembly and strut together define a plurality of detonation combustion regions in the gas flowpath upstream of the inner wall assembly.
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公开(公告)号：US20190241262A1
公开(公告)日：2019-08-08
申请号：US16269515
申请日：2019-02-06
摘要： A hypersonic vehicle includes a body; a first engine secured to the body, the first engine is configured to create forward thrust at a first flight regime; a second engine secured to the body, the second engine is configured to create forward thrust at a second flight regime; and the hypersonic vehicle transitions between the first engine and the second engine during the first flight regime and the second flight regime.
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公开(公告)号：US20180347508A1
公开(公告)日：2018-12-06
申请号：US15613189
申请日：2017-06-03
申请人： Dennis S. Lee
发明人： Dennis S. Lee
摘要： A machine (10) with lifting system (18) includes a method for generating a resultant force (424) from circulating toroidal flow field (410) and poloidal flow field (420) within nearly confined toroid volume (413). The machine (10) architecture has designs for adaptability at assembly level to achieve modularity for ease of fabrication, maintenance, and operations.
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公开(公告)号：US10006407B1
公开(公告)日：2018-06-26
申请号：US13481204
申请日：2012-05-25
申请人： Brian J. Tillotson
发明人： Brian J. Tillotson
CPC分类号： F02K7/08 , B64G1/401 , B64G1/409 , F02K99/00 , F24S23/30 , F24S40/55 , F24S70/60 , Y02E10/44 , Y02T50/671
摘要： An optical heat exchanger and an associated system and method are provided to allow a vehicle, such as an unmanned air vehicle, a rocket or the like, to deliver more payload at a lower cost. The optical heat exchanger includes a support surface defining a plurality of tapered openings. Each tapered opening tapers from the first size proximate an outwardly facing end of the opening to a second smaller size proximate an inwardly facing end of the opening. The inwardly facing end of each tapered opening is in communication with the propellant. The optical heat exchanger also includes a plurality of lenses with each lens positioned proximate the outwardly facing end of a respective opening. Each lens is configured to receive an electromagnetic energy beam and concentrate the majority of the electromagnetic energy beam through the inwardly facing end of the respective tapered opening, thereby heating the propellant.
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公开(公告)号：US20160096604A1
公开(公告)日：2016-04-07
申请号：US14877594
申请日：2015-10-07
CPC分类号： F02K7/08 , B63G8/08 , B63G2008/002 , B82Y15/00 , B82Y30/00 , B82Y40/00 , B82Y99/00 , Y10S977/902
摘要： In one general aspect, an apparatus can include a controller and a fuel container. The apparatus can include a propulsion device including a carbon nanotube structure including a parallel array of micro-channels configured to receive the fuel. Each of the micro-channels included in the array of micro-channels can have a length:width aspect ratio greater than 40:1 and can include a catalyst.
摘要翻译： 在一个一般方面，装置可以包括控制器和燃料容器。 该装置可以包括包括碳纳米管结构的推进装置，该碳纳米管结构包括构造成接收燃料的微通道的平行阵列。 包括在微通道阵列中的每个微通道可以具有大于40:1的长度宽度纵横比，并且可以包括催化剂。
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公开(公告)号：US09273633B2
公开(公告)日：2016-03-01
申请号：US14048749
申请日：2013-10-08
申请人： Steven D. Spangler
发明人： Steven D. Spangler
CPC分类号： F02K7/08 , A63F2009/0013 , G09B23/12 , G09B23/24
摘要： An apparatus and method for use in conducting an eruption reaction are disclosed. The apparatus includes a catalytic solids container with a mouth and fluid egress opening and a trigger device or mechanism that allows for the controlled release of a catalytic solid into an eruptible fluid. The catalytic solids container may be adapted to be coupled to a container for an eruptible fluid.
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8.发明申请公开(公告)号：US20140182295A1
公开(公告)日：2014-07-03
申请号：US14115530
申请日：2012-05-09
申请人： François Falempin
发明人： François Falempin
IPC分类号： F02K7/08
摘要： The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant mixture into the detonation chamber (3) at at least one segment of the injection base (10).
摘要翻译： 本发明涉及具有这种发动机的连续爆震波发动机和飞机。 连续爆震波发动机（1）用燃料和氧化剂的爆炸混合物操作，并且特别包括包括喷射基座（10）的爆炸室（3），该喷射基座的长度沿开放线（17）限定， ，诸如在横向平面中形成具有细长形式的引爆室（3）以及设置成将燃料/氧化剂混合物喷射到爆炸室（3）中的至少一个喷射系统（4）的喷射系统（4） 注射基底（10）的段。
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9.发明授权Technique for high mixing rate, low loss supersonic combustion with solid hydrogen and liquid helium fuel 失效高混合速率，低损耗超音速燃烧与固体氢和液态氦燃料的技术
公开(公告)号：US6003300A
公开(公告)日：1999-12-21
申请号：US786673
申请日：1997-01-21
申请人： Stephen C. Bates
发明人： Stephen C. Bates
摘要： This invention relates to a fueling process that allows complete combustion with air in the combustor of an aircraft traveling at a speed greater than the speed of sound. A process is described to inject a jet of solid hydrogen particles admixed in liquid helium through the combustor wall to achieve extremely rapid mixing of hydrogen throughout the supersonic airstream of the combustor of a high speed vehicle. Mixing on a molecular scale is so rapid that complete and efficient combustion occurs within the combustor.
摘要翻译： 本发明涉及一种加油过程，其允许以飞行速度大于声速的飞行器的燃烧器中的空气完全燃烧。 描述了一种将通过燃烧器壁混合在液氦中的固体氢颗粒射流注入到高速车辆的燃烧器的整个超音速气流中极快地混合氢气的方法。 在分子尺度上进行混合是非常快速的，从而在燃烧器内发生完全有效的燃烧。
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公开(公告)号：US5317866A
公开(公告)日：1994-06-07
申请号：US946228
申请日：1992-09-18
摘要： A relatively low drag, completely free-flying, tubular vehicle comprises a body that defines a leading edge and a trailing edge and includes an external surface and an internal surface each extending from the leading to the trailing edge. The internal surface has an axially converging upstream section extending from the leading edge to a discontinuity that constitutes a throat in the vehicle. The internal surface also has an axially diverging downstream section extending from the throat to the trailing edge. The internal surface is configured to enable introduction and mixing of fuel into an airstream flowing therethrough, and to generate a shock wave when in flight. The shock wave is of such magnitude and direction as to create a hot spot that subsequently causes ignition and combustion of the fuel-air mixture. The combustion causes formation of a detonation bubble and migration of the associated wave front upstream to stabilize slightly downstream of the throat. The combustion of the fuel results in rapid expansion of combustion products, generating forward thrust against the internal surface of the vehicle.
摘要翻译： 相对较低的阻力，完全自由飞行的管状车辆包括限定前缘和后缘的主体，并且包括外表面和内表面，每个内表面从前缘延伸到后缘。 内表面具有从前缘延伸到在车辆中构成喉部的不连续部分的轴向会聚的上游部分。 内表面还具有从喉部延伸到后缘的轴向发散的下游部分。 内表面构造成能够将燃料引入和混合到流过其中的气流中，并且在飞行中产生冲击波。 冲击波具有如此大的程度和方向，以产生随后引起燃料 - 空气混合物点火和燃烧的热点。 燃烧引起爆炸泡的形成和相关的波前向上游的迁移，以在喉部稍微下游稳定。 燃料的燃烧导致燃烧产物的快速膨胀，产生抵靠车辆内表面的向前推力。
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