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公开(公告)号：US07188467B2
公开(公告)日：2007-03-13
申请号：US10955614
申请日：2004-09-30
申请人： James Edward Johnson
发明人： James Edward Johnson
IPC分类号： F02K3/02
摘要： A method for assembling a gas turbine engine includes providing a core engine, and providing a flade system including a flade stream augmentor positioned within a flade duct. The method also includes channeling airflow through the core engine to produce engine thrust, channeling airflow through the flade duct to produce engine thrust, and igniting a portion of the airflow channeled through the flade duct using the flade stream augmentor to increase the amount of thrust produced by the flade system.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括提供一种核心发动机，并提供一种包括定位在飞边管道内的落叶加油器的落叶系统。 该方法还包括引导通过核心发动机的气流以产生发动机推力，将气流引导通过飞行器管道以产生发动机推力，并且使用落叶流增压器点燃引导通过飞行器管道的气流的一部分，以增加产生的推力量 由淡菜系统。
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公开(公告)号：US20080141650A1
公开(公告)日：2008-06-19
申请号：US11611592
申请日：2006-12-15
申请人： James Edward Johnson
发明人： James Edward Johnson
CPC分类号： F02C3/067 , F01D17/162 , F02K3/06 , F02K3/072 , Y10T29/49245
摘要： A gas turbine engine assembly is provided. The gas turbine engine assembly includes a core engine. The gas turbine engine assembly further includes a first rotor spool including a first fan assembly, an intermediate-pressure turbine, and a first shaft. The first fan assembly includes a single stage fan assembly coupled upstream from the core engine. The intermediate-pressure turbine includes a single stage turbine coupled downstream from the core engine. The first shaft extends between the first fan assembly and the intermediate-pressure turbine. The gas turbine engine assembly further includes a second rotor spool including a second fan assembly, a low-pressure turbine, and a second shaft. The second fan assembly includes a single stage fan assembly coupled upstream from the first fan assembly. The low-pressure turbine includes a single stage turbine coupled downstream from the intermediate-pressure turbine. The second shaft extends between the second fan assembly and the low-pressure turbine. A method of assembling the same is provided.
摘要翻译： 提供燃气涡轮发动机组件。 燃气涡轮发动机组件包括核心发动机。 燃气涡轮发动机组件还包括第一转子线轴，其包括第一风扇组件，中压涡轮机和第一轴。 第一风扇组件包括从核心发动机上游耦合的单级风扇组件。 中压涡轮机包括从核心发动机下游耦合的单级涡轮机。 第一轴在第一风扇组件和中压涡轮机之间延伸。 燃气涡轮发动机组件还包括第二转子线轴，其包括第二风扇组件，低压涡轮机和第二轴。 第二风扇组件包括从第一风扇组件上游耦合的单级风扇组件。 低压涡轮机包括从中压涡轮机下游连接的单级涡轮机。 第二轴在第二风扇组件和低压涡轮机之间延伸。 提供了一种组装方法。
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公开(公告)号：US07216475B2
公开(公告)日：2007-05-15
申请号：US10719884
申请日：2003-11-21
申请人： James Edward Johnson
发明人： James Edward Johnson
CPC分类号： F02K3/077 , F02K1/386 , F02K3/065 , F05D2220/327 , F05D2250/611
摘要： An aft FLADE gas turbine engine includes a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, and a mixer downstream of the low pressure turbine section and in fluid communication with the fan bypass duct, and an aft FLADE turbine downstream of the mixer. At least one row of aft FLADE fan blades disposed radially outwardly of and connected to the aft FLADE turbine and radially extending across a FLADE duct circumscribing the fan bypass duct. The aft FLADE turbine may be a free turbine or connected to and rotatable with the low pressure turbine section. A power extraction apparatus may be disposed within the engine and drivenly connected to the aft FLADE turbine.
摘要翻译： 后FLADE燃气涡轮发动机包括驱动地连接到低压涡轮机部分的风扇部分，位于风扇部分和低压涡轮机部分之间的核心发动机，围绕核心发动机并与风扇部分流体连通的风扇旁路管道 以及在低压涡轮机部分下游并与风扇旁通管道流体连通的混合器，以及在混合器下游的后FLADE涡轮机。 至少一排后FLADE风扇叶片设置在尾部FLADE涡轮机的径向外部并且连接到尾部FLADE涡轮机，并且径向延伸跨越包围风扇旁路管道的FLADE管道。 后FLADE涡轮机可以是自由涡轮机，或者与低压涡轮机部分连接并可转动。 动力提取装置可以设置在发动机内并且被驱动地连接到后FLADE涡轮。
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公开(公告)号：US07140174B2
公开(公告)日：2006-11-28
申请号：US10955461
申请日：2004-09-30
申请人： James Edward Johnson
发明人： James Edward Johnson
IPC分类号： F02K3/02
CPC分类号： F02C7/042 , F02K7/16 , F05D2220/10
摘要： A method for assembling a gas turbine engine includes providing a core engine, an inner fan assembly, and a fladed fan assembly, coupling a plurality of airflow ducts to the engine including an inner fan duct for channeling airflow through the inner fan assembly, a core engine duct for channeling airflow through the core engine, a bypass fan duct for channeling the airflow around the core engine duct, a flade duct for channeling airflow through the fladed fan assembly, and a ram duct surrounding an upstream portion of the flade duct, and coupling a plurality of control valves to the engine to control an amount of airflow channeled through each of the ducts using the plurality of control valves.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括提供核心发动机，内部风扇组件和有风扇的风扇组件，将多个气流管道耦合到发动机，该发动机包括用于将气流引导通过内部风扇组件的内部风扇管道， 用于引导通过核心发动机的气流的引擎管道，用于引导围绕核心发动机管道的气流的旁路风扇管道，用于将气流引导通过所述有风扇的风扇组件的溢流管道，以及围绕所述挡风管的上游部分的柱塞管道，以及 将多个控制阀耦合到发动机，以使用多个控制阀来控制通过每个管道的气流量。
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公开(公告)号：US07134271B2
公开(公告)日：2006-11-14
申请号：US10982477
申请日：2004-11-05
摘要： An aft FLADE gas turbine engine including a fan section drivenly connected to a low pressure turbine section followed by an aft FLADE turbine having at least one row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine, and at least one thrust vectoring nozzle in pressurized fluid flow receiving communication with the FLADE duct. One embodiment of the engine includes spaced apart right and left hand FLADE exhaust nozzles in pressurized fluid flow receiving communication with the FLADE duct and offset from a main engine exhaust nozzle located downstream of the aft FLADE turbine. Right and left hand valves disposed in right and left hand ducts extending between a FLADE airflow manifold in pressurized fluid flow receiving communication with the FLADE duct may be used to vector thrust. The right and left hand FLADE exhaust nozzle may be fixed or thrust vectoring nozzles.
摘要翻译： 一种后FLADE燃气涡轮发动机，其包括驱动地连接到低压涡轮机部分和后FLADE涡轮机的风扇部分，所述后部FLADE涡轮机具有径向延伸穿过外部FLADE涡轮机的FLADE管道的至少一排后FLADE风扇叶片，以及至少一个 加压流体流中的推力矢量喷嘴与FLADE管道相通。 发动机的一个实施例包括间隔开的左右FLADE排气喷嘴，其与FLADE管道的加压流体流动接收连通并且与位于后FLADE涡轮机下游的主发动机排气喷嘴偏移。 设置在与FLADE管道的加压流体流动接收连通的FLADE气流歧管之间延伸的右侧和左侧管道中的右侧和左侧阀可用于向量推力。 右侧和左侧FLADE排气喷嘴可以是固定的或推力矢量喷嘴。
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公开(公告)号：US4064692A
公开(公告)日：1977-12-27
申请号：US583056
申请日：1975-06-02
CPC分类号： F02K3/075 , F02K3/077 , Y02T50/671
摘要： A design technique, method, and apparatus for varying the bypass ratio and modulating the flow of a gas turbine engine of the bypass type in order to achieve improved mixed mission performance. The disclosed preferred embodiments each include a gas flow control system for management of core and bypass stream pressure comprising diverter valve means downstream of the core engine to selectively mix or separate the core and bypass exhaust streams. The flow control system may also include variable geometry means for maintaining the engine inlet airflow at a matched design level at all flight velocities. Each preferred embodiment thus may be converted from a high specific thrust mixed flow cycle at supersonic velocities to a lower specific thrust separated flow turbofan system at subsonic velocities with a high degree of flow variability in each mode of operation, wherein the engine inlet airflow may be maintained at a matched design level at all engine velocities. To further improve flow flexibility and assist in maintaining the engine inlet airflow matched to a design level throughout a variable velocity range, the flow control system may include a split fan in conjunction with two concentric bypass ducts. The disclosed variable cycle engine techniques, methods, and apparatus result in significantly reduced inlet and after-body drag levels and result in significantly improved installed fuel consumption for mixed mission aircraft.
摘要翻译： 用于改变旁路比并调节旁路型燃气涡轮发动机的流量的设计技术，方法和装置，以实现改进的混合任务性能。 公开的优选实施例各自包括用于管理核心和旁路流压力的气体流量控制系统，其包括在核心发动机下游的分流阀装置，以选择性地混合或分离核心和旁路排气流。 流量控制系统还可以包括可变几何装置，用于在所有飞行速度下将引擎入口气流维持在匹配的设计水平。 因此，每个优选实施例可以从超音速的高比推力混合流动循环转换成亚音速下的较低特定推力分离流量涡扇风扇系统，在每个操作模式下具有高度的流量变化性，其中发动机入口气流可以是 在所有发动机速度下保持在匹配的设计水平。 为了进一步改善流动灵活性并有助于维持在整个可变速度范围内匹配到设计水平的发动机入口气流，流量控制系统可以包括与两个同心旁路管道结合的分流风扇。 所公开的可变循环发动机技术，方法和装置导致入口和后体阻力水平显着降低，并且导致混合任务飞机的安装燃料消耗的显着改善。
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