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公开(公告)号：US20180179953A1
公开(公告)日：2018-06-28
申请号：US15390105
申请日：2016-12-23
发明人： Venkat Eswarlu Tangirala , Andrew Maxwell Peter , Kapil Kumar Singh , Keith Robert McManus , Joel Haynes , Anthony Dean
CPC分类号： F02C5/02 , F02C3/04 , F02C3/14 , F02C3/16 , F02C3/165 , F02C5/00 , F02C5/10 , F02C7/264 , F02K7/075 , F02K7/08 , F05D2220/32 , F05D2240/35 , F23R3/286 , F23R3/34 , F23R3/42 , F23R3/56 , F23R7/00
摘要： A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.
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公开(公告)号：US09752453B2
公开(公告)日：2017-09-05
申请号：US14793377
申请日：2015-07-07
发明人： George D. Rupp , Trajaen J. Troia
CPC分类号： F01D17/12 , F01D5/02 , F01D9/04 , F02C7/042 , F02K3/02 , F02K7/075 , F02K7/16 , F02K7/20 , F05D2220/10 , F05D2300/502 , Y02T50/672
摘要： The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.
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公开(公告)号：US20130177392A1
公开(公告)日：2013-07-11
申请号：US13781584
申请日：2013-02-28
发明人： George D. Rupp , Trajaen J. Troia
IPC分类号： F04D3/00
CPC分类号： F01D17/12 , F01D5/02 , F01D9/04 , F02C7/042 , F02K3/02 , F02K7/075 , F02K7/16 , F02K7/20 , F05D2220/10 , F05D2300/502 , Y02T50/672
摘要： The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.
摘要翻译： 本发明涉及一种机械系统和方法，其调节与整合中等涡轮发动机和诸如恒定体积燃烧室（CVC）排列的高马赫发动机的飞机发动机结合使用的飞行器入口扩散器中的气流，或 冲压喷气式排气装置，与涡轮机共同形成进气口。 调制系统使用两个铰接部件，一个可移动的空气流动管道和一个铰接锥体。 处于第一位置的空气流动管道处于与来自涡轮机的圆形进气面的第一位置专用气流连通，以从进气扩散器接收空气。 在该配置中，可膨胀锥体处于缩回位置，并且不会使气流重定向，并允许飞行器以低速模式操作，因为只有涡轮喷气机接收气流。 在过渡速度模式中，空气流动管道缩回以允许空气流动到涡轮喷气机和CVC。 铰链锥体完全覆盖涡轮喷气圆形进气面，将空气仅引导到高马赫飞机发动机，以使飞机能够以高速运行。
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公开(公告)号：US20110030340A1
公开(公告)日：2011-02-10
申请号：US12988604
申请日：2009-04-16
IPC分类号： F02K5/02
CPC分类号： F02B71/06 , F02K7/02 , F02K7/06 , F02K7/075 , Y02T50/672
摘要： According to the invention, the said engine (I), which comprises at least one flame tube (2) with a mobile transverse end wall (18), comprises an external envelope (3) around the said flame tube (2), which defines a peripheral annular space (4) in which fixed flow guides (11, 12, 13, 14) are positioned, these flow guides forming flow channels (10) for the air, and at least one mobile plug (25), connected to the said mobile end wall (18), to close off and open one of the flow channels (10).
摘要翻译： 根据本发明，所述发动机（I）包括具有可动横向端壁（18）的至少一个火焰管（2），包括围绕所述火焰管（2）的外壳（3），其限定 固定的流动引导件（11,12,13,14）定位在其中，这些流动导向件形成用于空气的流动通道（10），以及至少一个移动塞（25），其连接到所述外部环形空间 所述移动端壁（18）关闭并打开所述流动通道（10）中的一个。
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公开(公告)号：US20070022740A1
公开(公告)日：2007-02-01
申请号：US11190263
申请日：2005-07-27
申请人： Richard Ouellette
发明人： Richard Ouellette
IPC分类号： F02K7/02
摘要： A pulsejet is provided that includes an inlet, an exhaust nozzle, and a combustion chamber between the inlet and the exhaust nozzle. The pulsejet additionally includes a flow-turning device positioned over an end of the inlet. The flow turning device forms an air flow pathway (AFP) having a substantially 180° turn. The 180° turn aligns a direction of exhaust exiting the combustion chamber through the inlet along a positive axial thrust line and substantially parallel with exhaust exiting the combustion chamber through the nozzle.
摘要翻译： 提供脉冲喷射器，其包括入口和排气喷嘴以及在入口和排气喷嘴之间的燃烧室。 脉冲喷射还包括位于入口端部的流动转向装置。 流动转向装置形成具有大致180°回转的空气流通路径（AFP）。 180°转角沿着正的轴向推力线，通过入口排出离开燃烧室的排气的方向，并且基本上平行于通过喷嘴离开燃烧室的排气。
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公开(公告)号：US07062901B1
公开(公告)日：2006-06-20
申请号：US11183133
申请日：2005-07-15
摘要： The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled to the at least one periodic combustion chamber. The supersonic exhaust nozzle is configured with a variable exhaust expansion ratio.
摘要翻译： 所公开的装置指向周期性燃烧推进系统。 周期性燃烧推进系统包括至少一个周期性燃烧室，其被配置为容纳周期性燃烧，以及至少一个超音速排气喷嘴，其联接到所述至少一个周期性燃烧室。 超音速排气喷嘴配置有可变的排气膨胀比。
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公开(公告)号：US06981365B1
公开(公告)日：2006-01-03
申请号：US10331176
申请日：2002-12-26
摘要： The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled to the at least one periodic combustion chamber. The supersonic exhaust nozzle is configured with a variable exhaust expansion ratio.
摘要翻译： 所公开的装置指向周期性燃烧推进系统。 周期性燃烧推进系统包括至少一个周期性燃烧室，其被配置为容纳周期性燃烧，以及至少一个超音速排气喷嘴，其联接到所述至少一个周期性燃烧室。 超音速排气喷嘴配置有可变的排气膨胀比。
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公开(公告)号：US20050103022A1
公开(公告)日：2005-05-19
申请号：US10929910
申请日：2004-08-30
申请人： Robert Kraft
发明人： Robert Kraft
CPC分类号： F23C15/00 , F02C5/02 , F02K3/08 , F02K7/02 , F02K7/075 , F05D2270/11 , F23R7/00 , Y02T50/671
摘要： A method for operating a pulse detonation system. The method includes providing a pulse detonation chamber including a plurality of detonation tubes extending therein, and detonating a mixture of fuel and air within each detonation tube such that at least a first tube is detonated at a different time than at least a second detonation tube.
摘要翻译： 一种操作脉冲爆震系统的方法。 该方法包括提供脉冲爆震室，其包括在其中延伸的多个爆管，并且在每个爆管内引爆燃料和空气的混合物，使得至少第一管在不同于至少第二爆管的时间内被引爆。
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公开(公告)号：US20040123582A1
公开(公告)日：2004-07-01
申请号：US10722158
申请日：2003-11-24
IPC分类号： F02C005/00
摘要： A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of combustion conduits in a circumferential array. Each conduit cyclically receives a charge and discharges combustion products of the charge. A venturi effect may help control fuel/air charge leakage from a flowpath spanning the carousel and a stationary manifold.
摘要翻译： 脉冲燃烧装置包括支撑结构和由支撑结构支撑并相对于其围绕轴线旋转的燃烧器转盘。 圆盘传送带具有多个周向排列的燃烧管道。 每个管道周期性地接收电荷并排出电荷的燃烧产物。 文丘里效应可以帮助控制从圆盘传送带和固定歧管的流路中的燃料/空气电荷泄漏。
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公开(公告)号：US20040112060A1
公开(公告)日：2004-06-17
申请号：US10316800
申请日：2002-12-11
发明人： Robert Eugene Kraft
IPC分类号： F02C005/00
CPC分类号： F23C15/00 , F02C5/02 , F02K3/08 , F02K7/02 , F02K7/075 , F05D2270/11 , F23R7/00 , Y02T50/671
摘要： A method for operating a pulse detonation system. The method includes providing a pulse detonation chamber including a plurality of detonation tubes extending therein, and detonating a mixture of fuel and air within each detonation tube such that at least a first tube is detonated at a different time than at least a second detonation tube.
摘要翻译： 一种操作脉冲爆震系统的方法。 该方法包括提供脉冲爆震室，其包括在其中延伸的多个爆管，并且在每个爆管内引爆燃料和空气的混合物，使得至少第一管在不同于至少第二爆管的时间内被引爆。
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