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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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公开(公告)号：US5253474A
公开(公告)日：1993-10-19
申请号：US753139
申请日：1991-08-30
摘要： A supersonic combustion ramjet having a supersonic combustor. The supersonic combustor has a backward-facing step formed in a wall thereof and a forward-facing ramp formed in the wall downstream from the step. Hydrogen fuel is injected into the air flow by axially-directed fuel injectors disposed in the step and/or normally-directed fuel injectors disposed in the ramp. The ramp is inclined toward the center of the combustor so that fuel from the fuel injectors is turned into the main flow. The ensures rapid mixing which enables combustion to be completed within a distance on the order of one foot.
摘要翻译： 具有超音速燃烧器的超音速燃烧冲压式喷气式发动机。 超音速燃烧器具有在其壁中形成的向后的台阶和形成在台阶下游的壁中的前向斜面。 通过设置在设置在斜坡中的台阶和/或正常定向的燃料喷射器中的轴向定向的燃料喷射器将氢燃料喷射到空气流中。 斜坡朝向燃烧器的中心倾斜，使得来自燃料喷射器的燃料变成主流。 确保快速混合，使燃烧在一英尺数量级的距离内完成。
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13.发明授权Ram jet engine construction and a valve control for proportioning fuel rich gas of ram jet rocket engines 失效Ram喷气发动机结构和用于比例喷射式火箭发动机的富燃气体的阀门控制
公开(公告)号：US4449361A
公开(公告)日：1984-05-22
申请号：US354627
申请日：1982-03-04
申请人： Thomas Hahnel
发明人： Thomas Hahnel
摘要： A ram jet engine comprises a wall structure defining a precombustion chamber having a solid fuel which when ignited can raise fuel rich gases which flow through a valve housing passage and into a main combustion chamber where final combustion takes place. A valve is provided in the valve housing which includes a shaft portion which is driven for example by an electric motor to rotate a valve body between two end positions in which the valve body is shifted from a position substantially blocking off all flow through the valve passage to one in which it permits a maximum preselected flow. The valve body is advantageously journalled on a shaft and is provided with a hub portion which embraces the shaft and protects it from the hot gases. The valve body is shaped as a cylindrical wedge tapering from the widest portion of one end to a narrowest portion at the opposite end. The valve body is oriented in the valve passage so that with its widest end facing the precombustion chamber it substantially blocks off the flow of the gas. When it is rotated so that its narrowest end faces toward the precombustion chamber a maximum amount of gas flow as desired is permitted to flow through the passage.
摘要翻译： 冲压式喷气式发动机包括限定具有固体燃料的预燃室的壁结构，其在点燃时可以提高流过阀壳体通道并进入发生最终燃烧的主燃烧室的富含燃料的气体。 阀门设置在阀壳体中，其包括轴部分，该轴部分由电动机驱动，以使阀体在两个端部位置之间旋转，阀体从基本上阻挡所有通过阀通道的流动的位置移动 其中允许最大预选流量。 阀体有利地轴颈安装在轴上并且设置有包围轴并且保护其免受热气体的毂部分。 阀体形成为从相对端的一端的最宽部分到最窄部分的圆柱形楔形件。 阀体在阀通道中定向，使得其最宽端面向预燃室，其基本上阻挡气体的流动。 当其旋转使得其最窄端朝向预燃室时，允许所需的最大量的气流流过通道。
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公开(公告)号：US4118929A
公开(公告)日：1978-10-10
申请号：US778424
申请日：1977-03-17
申请人： Thomas H. Sharpe
发明人： Thomas H. Sharpe
摘要： An impaction augmented jet engine with a primary burner unit and a primary impaction/induction unit which separates a portion of the exhaust gases from the burner unit for recirculation thereto and also separates fresh air by impaction and induction for mixing with the separated exhaust gases to supply the burner unit. The engine also includes an induction ram burner unit downstream of the primary burner unit so that the exhaust gases from the primary burner unit augment the fresh air passing into the induction ram burner unit for combustion.
摘要翻译： 具有主要燃烧器单元和主要冲击/感应单元的冲击增强喷气发动机，其将一部分废气与燃烧器单元分离以用于再循环，并且还通过冲击和感应分离新鲜空气，以与分离的废气混合供应 燃烧器单元。 发动机还包括在主燃烧器单元下游的感应压头燃烧器单元，使得来自主燃烧器单元的排气增加通过感应冲压燃烧器单元的新鲜空气进行燃烧。
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公开(公告)号：US3864907A
公开(公告)日：1975-02-11
申请号：US41285973
申请日：1973-11-05
申请人： US AIR FORCE
发明人： CURRAN EDWARD T
CPC分类号： F02K7/10
摘要： A supersonic combustion ramjet having a combustor including at least two constant area combustor chamber-sections or stages disposed in open communication between the ramjet inlet and expansion nozzle, and further each incorporating a combustion stabilizing step configuration and a separate fuel injector for respectively and selectively adding heat to the pair of constant area-chambers to control the heat addition to the subsonic or supersonic mode.
摘要翻译： 超音速燃烧冲压式喷气式发动机具有燃烧器，该燃烧器包括至少两个恒定区域的燃烧室室部分或台阶，其设置在冲压喷气进口和膨胀喷嘴之间的开放连通中，并且还包括燃烧稳定步骤构型和单独的燃料喷射器， 加热到一对恒定区域室以控制亚音速或超音速模式的加热。
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公开(公告)号：US3541795A
公开(公告)日：1970-11-24
申请号：US3541795D
申请日：1967-08-17
申请人： GEN KINETICS CORP
发明人： NELSON DANIEL E
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公开(公告)号：US3425223A
公开(公告)日：1969-02-04
申请号：US3425223D
申请日：1967-03-07
发明人： BROWNING JAMES A
CPC分类号： F03H1/00
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公开(公告)号：US2945345A
公开(公告)日：1960-07-19
申请号：US66977457
申请日：1957-07-03
申请人： HOFFMANN GEORGE R
发明人： HOFFMANN GEORGE R
IPC分类号： F02K7/08
CPC分类号： F02K7/08
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公开(公告)号：US2624281A
公开(公告)日：1953-01-06
申请号：US77328347
申请日：1947-09-10
申请人： MCNALLY JAMES A
发明人： MCNALLY JAMES A
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