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公开(公告)号：US08695324B2
公开(公告)日：2014-04-15
申请号：US12796353
申请日：2010-06-08
IPC分类号： F02K3/02
CPC分类号： F02C3/064 , F01D5/022 , F02K3/077 , Y02T50/672
摘要： A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform.
摘要翻译： 公开了一种具有外部风扇系统的风扇组件，风扇组件包括从弧形平台径向向外延伸的外部风扇第一级和外部风扇第二级。
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公开(公告)号：US20110120082A1
公开(公告)日：2011-05-26
申请号：US12796353
申请日：2010-06-08
IPC分类号： F02K3/02
CPC分类号： F02C3/064 , F01D5/022 , F02K3/077 , Y02T50/672
摘要： A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform.
摘要翻译： 公开了一种具有外部风扇系统的风扇组件，风扇组件包括从弧形平台径向向外延伸的外部风扇第一级和外部风扇第二级。
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公开(公告)号：US07246484B2
公开(公告)日：2007-07-24
申请号：US10647881
申请日：2003-08-25
CPC分类号： F02K3/072 , F02K3/077 , F05D2220/327 , Y02T50/671
摘要： An exemplary embodiment of a FLADE counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to one of axially spaced-apart first and second counter-rotatable fans. A core engine located downstream and axially aft of the first and second counter-rotatable fans is circumscribed by a fan bypass duct downstream and axially aft of the first and second counter-rotatable fans. The row of FLADE fan blades radially extend across a FLADE duct circumscribed about the first and second counter-rotatable fans and the fan bypass duct. A second low pressure turbine is drivingly connected to the first counter-rotatable fan and a first low pressure turbine is drivingly connected to the second counter-rotatable fan.
摘要翻译： FLADE反向旋转风扇飞行器燃气涡轮发动机的示例性实施例包括至少一排FLADE风扇叶片，其设置在轴向间隔开的第一和第二可逆旋转风扇之间的径向外侧并且驱动地连接到轴向间隔开的第一和第二可逆旋转风扇中的一个。 位于第一和第二反向旋转风扇的下游和轴向后部的核心发动机由第一和第二可逆旋转风扇的下游和轴向后部的风扇旁路管道限定。 一排FLADE风扇叶片径向延伸穿过围绕第一和第二可逆转风扇和风扇旁通管道的FLADE管道。 第二低压涡轮机驱动地连接到第一可逆旋转风扇，并且第一低压涡轮机驱动地连接到第二可逆转风扇。
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公开(公告)号：US20110120083A1
公开(公告)日：2011-05-26
申请号：US12796372
申请日：2010-06-08
IPC分类号： F02K3/02
CPC分类号： F02C3/064 , F01D5/022 , F02K3/077 , Y02T50/672
摘要： A gas turbine engine comprising an outer fan system is disclosed, having an outer fan first stage having a circumferential row of outer fan first blades, an outer fan second stage having a circumferential row of outer fan second blades located axially aft from the outer fan first stage wherein the outer fan first stage and the outer fan second stage are adapted to rotate with the fan rotor.
摘要翻译： 公开了一种包括外风扇系统的燃气涡轮发动机，其具有外风扇第一级，其具有圆周排的外风扇第一叶片;外风扇第二级，其具有周向列的外风扇第二叶片，所述外风扇第二叶片从外风扇第一 其中外风扇第一级和外风扇第二级适于与风扇转子一起旋转。
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公开(公告)号：US07631484B2
公开(公告)日：2009-12-15
申请号：US11308219
申请日：2006-03-13
IPC分类号： F02K3/02
CPC分类号： F02K3/062 , F02C3/073 , F02C7/042 , F05D2240/80 , Y02T50/672
摘要： A fan assembly for a gas turbine engine includes a turbine rotor adapted to be disposed aft of a core of the gas turbine engine; a row of turbine blades carried by the rotor, each turbine blade extending from the rotor to a tip, the turbine blades adapted to extract energy from a stream of pressurized combustion gases generated by the core; and at least two rows of axially-spaced apart, radially-extending fan blades carried by the row of turbine blades for rotation therewith.
摘要翻译： 一种用于燃气涡轮发动机的风扇组件，包括适于设置在燃气涡轮发动机的核心的后方的涡轮转子; 由转子承载的一排涡轮叶片，每个涡轮叶片从转子延伸到尖端，涡轮机叶片适于从由芯产生的加压燃烧气体流中提取能量; 以及至少两排轴向间隔开的径向延伸的风扇叶片，所述风扇叶片由所述一排涡轮机叶片承载以与其一起旋转。
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公开(公告)号：US08622687B2
公开(公告)日：2014-01-07
申请号：US12871073
申请日：2010-08-30
IPC分类号： F02K3/00
CPC分类号： F02K3/075 , F05D2220/323
摘要： A method of operating a compressor in an adaptive core engine is disclosed. The method comprises the steps of operating a front block compressor to increase pressure of a fluid to a first pressure ratio in a high-power mode operation; operating a rear block compressor coupled to the front block compressor such that the front block compressor and the rear block compressor operate at the same physical speed; closing a rear block stator vane located axially forward from the rear block compressor such that the flow of the fluid into the rear block compressor is substantially cut off; and keeping a blocker door opened such that substantially all of the fluid pressurized by the front block compressor flows through a bypass passage during the high-power mode operation. The operation may be transitioned from the high-power mode to a low-power mode by opening a rear block stator such that the rear block compressor receives at least a portion of the fluid flowing from the front block compressor and maintains an overall engine pressure ratio.
摘要翻译： 公开了一种在自适应核心引擎中操作压缩机的方法。 该方法包括以下步骤：在高功率模式操作中操作前部块压缩机以将流体的压力增加到第一压力比; 操作联接到前部块压缩机的后部块式压缩机，使得前部块式压缩机和后部块式压缩机以相同的物理速度运行; 关闭从后块式压缩机轴向向前定位的后块定子叶片，使得流入后块式压缩机的流体基本上被切断; 并且保持阻挡门打开，使得在大功率模式操作期间，由前块式压缩机加压的基本上所有的流体都流经旁路通道。 操作可以通过打开后挡块定子从大功率模式转换到低功率模式，使得后块式压缩机接收从前块式压缩机流出的流体的至少一部分，并保持总体发动机压力比 。
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公开(公告)号：US07509797B2
公开(公告)日：2009-03-31
申请号：US11118171
申请日：2005-04-29
申请人： James Edward Johnson
发明人： James Edward Johnson
IPC分类号： F02K1/00
摘要： A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A thrust vectoring system is joined between a compressor and the nozzle. A controller is operatively joined to the thrust vectoring system for selectively varying distribution of air bled from the compressor into the exhaust nozzle for vectoring propulsion thrust.
摘要翻译： 涡轮喷气发动机包括核心发动机，加力燃烧器和串联流动通信中的会聚发散排气喷嘴。 推力矢量系统连接在压缩机和喷嘴之间。 控制器可操作地连接到推力矢量系统，用于选择性地改变从压缩机排放到排气喷嘴中的空气分配，用于矢量推进推力。
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公开(公告)号：US07877980B2
公开(公告)日：2011-02-01
申请号：US11617371
申请日：2006-12-28
申请人： James Edward Johnson
发明人： James Edward Johnson
IPC分类号： F02K3/02
摘要： A gas turbine engine includes a turbomachinery core operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan disposed upstream of the core, the fan adapted to extract energy from the core and generate a first flow of air which is compressed at a first pressure ratio; and at least a first bypass duct surrounding the core downstream of the fan adapted to selectively receive at least a first selected portion of the first flow which is compressed at a second pressure ratio lower than the first pressure ratio, and to bypass the first selected portion around the core, thereby varying a bypass ratio of the engine. The fan is adapted to maintain a flow rate of the first flow substantially constant, independent of the bypass ratio.
摘要翻译： 燃气涡轮发动机包括涡轮机芯，其可操作以产生可变流量的加压燃烧气体流，同时保持基本上恒定的芯压比; 设置在所述芯的上游的旋转风扇，所述风扇适于从所述芯提取能量并产生以第一压力比压缩的第一空气流; 以及至少第一旁路管道，围绕所述风扇下游的所述核心，适于选择性地接收所述第一流动的第一选定部分，所述第一流量以比所述第一压力比低的第二压力比被压缩，并绕过所述第一选定部分 围绕芯部，从而改变发动机的旁路比。 风扇适于保持第一流量的流量基本上恒定，而与旁路比无关。
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公开(公告)号：US07424805B2
公开(公告)日：2008-09-16
申请号：US11118967
申请日：2005-04-29
申请人： James Edward Johnson
发明人： James Edward Johnson
IPC分类号： F02K3/10
摘要： A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A controller is operatively joined to the core engine and afterburner and configured for scheduling fuel thereto for operating the afterburner dry during subsonic flight operation of the engine, wet during transonic flight, and dry during supersonic flight.
摘要翻译： 涡轮喷气发动机包括核心发动机，加力燃烧器和串联流动通信中的会聚发散排气喷嘴。 控制器可操作地连接到核心发动机和加力燃烧器，并被配置为用于调度燃料以在发动机的亚音速飞行操作期间干燥加热器，在跨音速飞行期间湿润，并且在超音速飞行期间干燥。
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公开(公告)号：US07395657B2
公开(公告)日：2008-07-08
申请号：US10689289
申请日：2003-10-20
申请人： James Edward Johnson
发明人： James Edward Johnson
CPC分类号： B64D33/02 , B64D2033/026
摘要： An aircraft propulsion system includes a gas turbine engine having a fan section, at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to the fan section, the row of FLADE fan blades radially extending across a FLADE duct circumscribing the fan section, an engine inlet including a fan inlet to the fan section and an annular FLADE inlet to the FLADE duct. A fixed geometry inlet duct is in direct flow communication with the engine inlet. The fan section may include only a single direction of rotation fan or alternatively axially spaced apart first and second counter-rotatable fans in which the FLADE fan blades are drivingly connected to one of the first and second counter-rotatable fans. The row of FLADE fan blades may be disposed between rows of variable first and second FLADE vanes.
摘要翻译： 飞机推进系统包括具有风扇部分的燃气涡轮发动机，至少一排FLADE风扇叶片，其设置在风扇部分的径向外部并且驱动地连接到风扇部分，FLADE风扇叶片排沿径向延伸穿过限定风扇部分的FLADE管道 一个发动机入口，其包括风扇部分的风扇入口和FLADE管道的环形FLADE入口。 固定的几何形状入口管道与发动机入口直接流动连通。 风扇部分可以仅包括单个方向的旋转风扇或备选地轴向间隔开的第一和第二可逆旋转风扇，其中FLADE风扇叶片驱动地连接到第一和第二可逆旋转风扇中的一个。 FLADE风扇叶片的行可以设置在可变的第一和第二FLADE叶片的行之间。
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