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公开(公告)号：US20040123583A1
公开(公告)日：2004-07-01
申请号：US10334019
申请日：2002-12-30
IPC分类号： F02C005/00
摘要： Distributed initiation (e.g., multipoint or continuous) is utilized to obtain constant volume-like combustion performance in a pulse combustion device in the absence of detonation. A number of such devices may be utilized as turbine engine combustors.
摘要翻译： 在不存在爆震的情况下，利用分布式启动（例如，多点或连续）来获得脉冲燃烧装置中恒定体积的燃烧性能。 许多这样的装置可以用作涡轮发动机燃烧器。
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公开(公告)号：US20040118972A1
公开(公告)日：2004-06-24
申请号：US10245145
申请日：2002-09-16
IPC分类号： B64C027/22
CPC分类号： B64C29/0058 , F02K7/02 , F02K7/075 , Y02T50/671
摘要： A vertical take-off and landing (VTOL) aircraft includes separate axial and vertical propulsion sources. The vertical propulsion source includes pulsejet engines located in separate augmentor bays having apertured walls to equalize pulsejet thrust. The pulsejet engine structure is integrated with aircraft structure such that aircraft structural loads are partially carried by each pulsejet engine. Each pulsejet engine produces an aircraft vertical thrust component throttled or exhaust restricted to control aircraft ascent or descent separate from the axial propulsion source. One or more inlet cowls isolate the pulsejet engine bays. One or more outlet cowls at the exhaust bays assist in controlling pulsejet engine thrust. By using separate axial and vertical thrust sources and pulsejet engines for vertical thrust, aircraft speed, payload and operating range are improved and loss of one or more lift engines is mitigated compared to VTOL aircraft using a single propulsion source type for axial and vertical thrust.
摘要翻译： 垂直起降飞机包括独立的轴向和垂直推进源。 垂直推进源包括位于具有多孔壁的单独增强器舱中的脉冲喷气发动机，以均衡脉冲喷射推力。 脉冲喷气发动机结构与飞机结构集成，使得飞机结构载荷由每个脉冲喷气发动机部分承载。 每个脉冲喷气发动机产生一个飞机垂直推力组件节流或排气限制，以控制与轴向推进源分离的飞机上升或下降。 一个或多个入口罩隔离脉冲喷气发动机舱。 在排气槽处的一个或多个出口罩有助于控制脉冲喷气发动机推力。 通过使用单独的轴向和垂直推力源和脉冲喷气发动机用于垂直推力，与使用单个推进源类型用于轴向和垂直推力的垂直起降飞机相比，改进了飞机速度，有效载荷和操作范围，减轻了一个或多个提升发动机的损失。
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公开(公告)号：US06439503B1
公开(公告)日：2002-08-27
申请号：US09612727
申请日：2000-07-10
IPC分类号： B64B124
CPC分类号： B64D27/16 , F02K7/06 , F02K7/075 , F05D2250/231 , Y02T50/44
摘要： A pulse detonation cluster includes a cluster housing and a plurality of pulse detonation engines mounted within the housing. Each pulse detonation engine has an inner tubular housing rigidly and concentrically mounted within a cylindrical bore of an outer tubular housing. The inner housing has a plurality of inner housing ports, and the outer housing has a plurality of outer housing ports. A detonation chamber is formed in the annulus between the inner housing and the outer housing. An outer valve sleeve is rotatably mounted to the outer housing for selectively allowing air to enter the detonation chamber through the outer housing ports. A fuel delivery member is aligned with each inner housing port to deliver fuel to the detonation chamber through the inner housing ports. An inner sleeve is mounted to the inner housing to protect the fuel delivery members during detonation. The air and fuel mixture is detonated by several igniters located in the detonation chamber. The detonation creates a detonation wave that travels through an open downstream end of the detonation chamber, thereby creating thrust for the engine. When combined in the cluster housing, outer valve sleeves of the pulse detonation engines are rotated by a common gear, which allows the engines to be easily timed to share inlet air entering the cluster housing. A pulse detonation bank is a combination of two or more pulse detonation clusters within a bank housing having a bank inlet. All of the pulse detonation engines within the bank share the bank inlet and are timed to maximize consumption of inlet air.
摘要翻译： 脉冲爆震簇包括集群壳体和安装在壳体内的多个脉冲爆震引擎。 每个脉冲爆震发动机具有刚性且同心地安装在外部管状壳体的圆柱形孔内的内部管状壳体。 内壳体具有多个内壳体端口，并且外壳体具有多个外壳体端口。 在内壳体和外壳体之间的环形空间中形成有爆震室。 外部阀套可旋转地安装到外壳上，用于选择性地允许空气通过外部壳体端口进入引爆室。 燃料输送构件与每个内壳体口对准，以通过内壳体端口将燃料输送到爆震室。 内部套筒安装到内部壳体以在引爆期间保护燃料输送构件。 空气和燃料混合物由位于爆炸室中的几个点火器引爆。 爆震产生一个穿过爆炸室的下游开口的爆震波，从而产生发动机的推力。 当组合在集群壳体中时，脉冲爆震发动机的外部阀套由普通齿轮旋转，这允许发动机容易地定时地共享进入集群壳体的入口空气。 脉冲爆炸堤是具有堤岸入口的堤岸外壳内的两个或多个脉冲爆震簇的组合。 银行内的所有脉冲爆震引擎共享银行入口，并计时以最大限度地吸收入口空气。
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公开(公告)号：US5873240A
公开(公告)日：1999-02-23
申请号：US662858
申请日：1996-06-12
摘要： A pulse detonation rocket engine, having at least two detonation chambers. The rocket propelled vehicle includes at least one fuel delivery system in fluid communication with each of the at least two detonation chambers, and at least one oxidant delivery system in fluid communication with the detonation chambers, along with fast-acting valves to inject fuel and oxidant controlledly into the chambers. An ignitor in each of the detonation chambers intermittently initiates detonation of a fuel and oxidant mixture in the chamber, in a controlled cycle, to provide motive force. Also provided is a combined cycle engine, able to operate in air breathing mode, oxidant augmented mode, and as a rocket engine. The combined cycle engine includes at least one detonation chamber, and may include a plurality of such chambers. The invention further provides methods of intermittently detonating sequentially created fuel and oxygen mixtures in these engines, and methods of using these engines.
摘要翻译： 具有至少两个爆震室的脉冲爆震火箭发动机。 火箭推进车辆包括与至少两个爆炸室中的每一个流体连通的至少一个燃料输送系统，以及与爆震室流体连通的至少一个氧化剂输送系统，以及用于喷射燃料和氧化剂的快速作用阀 受控地进入房间。 每个引爆室中的点火器在受控循环中间歇地启动燃料和氧化剂混合物的爆炸，以提供动力。 还提供了能够在空气呼吸模式，氧化剂增强模式和作为火箭发动机中操作的联合循环发动机。 联合循环发动机包括至少一个爆震室，并且可以包括多个这样的室。 本发明还提供了在这些发动机中间歇地引爆依次产生的燃料和氧气混合物的方法，以及使用这些发动机的方法。
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35.发明授权Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine 失效从气体涡轮发动机主流路径喷射外来物的方法和装置
公开(公告)号：US5123240A
公开(公告)日：1992-06-23
申请号：US495660
申请日：1990-03-19
申请人： Wilson Frost , Peter J. Wood , Melvin Bobo , Daniel R. Little
发明人： Wilson Frost , Peter J. Wood , Melvin Bobo , Daniel R. Little
摘要： A method and apparatus are disclosed for treating ice and debris in a gas turbine engine. More particularly, a specially configured and slidable scoop is positioned between the booster exit and the compressor inlet in a gas turbine engine. An actuator mechanism can be coupled through a linkage to the scoop to position the scoop within the core path at low power conditions and retract the scoop from the core flow path at high power conditions.
摘要翻译： 公开了一种用于处理燃气涡轮发动机中的冰和碎屑的方法和装置。 更具体地，特别构造和可滑动的铲斗位于燃气涡轮发动机的增压出口和压缩机入口之间。 致动器机构可以通过连接件与铲斗相连接，以将铲斗定位在低功率条件下的核心路径内，并且在高功率条件下将铲斗从核心流动路径缩回。
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公开(公告)号：US2750733A
公开(公告)日：1956-06-19
申请号：US35007253
申请日：1953-04-21
申请人： SNECMA
发明人： PARIS FRANCOIS G , LE FOLL JEAN , BERTIN JEAN H , BARAUT MARCEL J
IPC分类号： F02K7/075
CPC分类号： F02K7/075
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公开(公告)号：US2500712A
公开(公告)日：1950-03-14
申请号：US65218046
申请日：1946-03-05
申请人： POUND SERRELL JESSE
发明人： POUND SERRELL JESSE
IPC分类号： F02K7/075
CPC分类号： F02K7/075 , Y02T50/671
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公开(公告)号：US20150377060A1
公开(公告)日：2015-12-31
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.
摘要翻译： 本发明涉及一种机械系统，其调节飞行器入口漫射器中的气流，该飞行器入口漫射器与与中等涡轮发动机和诸如恒定体积燃烧器（CVC）布置或冲压喷气装置的高马赫发动机相结合的飞机发动机结合使用 进气口与涡轮机共同形成。 调制系统使用铰接锥。 当处于缩回位置时，铰接锥体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。 在最广泛的地方，铰接锥完全覆盖涡轮喷气圆形进气面，排除了涡轮发动机的运行。
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公开(公告)号：US09103280B2
公开(公告)日：2015-08-11
申请号：US13781584
申请日：2013-02-28
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 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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