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    Bifurcation and aft vent used to vary fan nozzle exit area
    4.
    发明授权
    Bifurcation and aft vent used to vary fan nozzle exit area 有权
    分岔和尾部通风口用于改变风扇喷嘴出口区域

    公开(公告)号：US08650854B2

    公开(公告)日：2014-02-18

    申请号：US12374336

    申请日：2006-10-12

    申请人： Edward F. Migliaro, Jr. ,  Michael Winter ,  Ashok K. Jain

    发明人： Edward F. Migliaro, Jr. ,  Michael Winter ,  Ashok K. Jain

    IPC分类号： F02K1/00

    CPC分类号： F02K1/15 ,  F02K1/30 ,  F02K3/06 ,  F05D2220/326 ,  F05D2220/327

    摘要： A turbofan engine includes a core nacelle housing a spool having a turbine. A turbofan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the turbofan and core nacelle. A bifurcation supports the core nacelle relative to the fan nacelle and extends radially between the nacelles. The core and fan nacelles provide a bypass flow path receiving bypass flow from the turbofan. In the example, the nacelles provide a fixed nozzle exit area. The bifurcation includes an inlet that is in communication with a passage. The passage is selectively opened and closed by a valve to provide air from the inlet to a vent opening near the nozzle exit area. By opening the valve, the nozzle exit area is effectively increased to provide increased bypass flow through the turbine engine.

    摘要翻译： 涡轮风扇发动机包括容纳具有涡轮的阀芯的核心机舱。 涡轮风扇布置在核心机舱的上游并联接到线轴。 风扇机舱围绕涡轮风扇和核心机舱。 分叉支撑相对于风扇机舱的核心机舱，并且在发动机舱之间径向延伸。 核心和风扇舱提供旁路流路，从涡轮风扇接收旁路流。 在该示例中，发动机舱提供固定的喷嘴出口区域。 分叉包括与通道连通的入口。 该通道由阀选择性地打开和关闭，以将空气从入口提供到喷嘴出口区域附近的通风口。 通过打开阀门，喷嘴出口区域被有效地增加，以提供通过涡轮发动机的增加的旁路流量。

    SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE
    5.
    发明申请
    SPEED SENSOR PROBE LOCATION IN GAS TURBINE ENGINE 审中-公开
    气动涡轮发动机速度传感器探头位置

    公开(公告)号：US20130192242A1

    公开(公告)日：2013-08-01

    申请号：US13368677

    申请日：2012-02-08

    申请人： Todd A. Davis ,  Brian P. Cigal

    发明人： Todd A. Davis ,  Brian P. Cigal

    IPC分类号： F02C9/28 ,  F02K3/00 ,  F02C7/00

    CPC分类号： F01D21/003 ,  F02C3/107 ,  F02C3/113 ,  F05D2220/326 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2270/021 ,  F05D2270/023 ,  F05D2270/304 ,  F05D2270/80 ,  Y02T50/671 ,  Y10T29/49231

    摘要： A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool, which is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. A second turbine is coupled through a second spool to drive the second compressor. A speed sensor probe is operable to determine a rotational speed of the first spool. The speed sensor probe is located axially aft of the first axial position and the second axial position.

    摘要翻译： 燃气涡轮发动机包括风扇，连接以驱动风扇的风扇驱动齿轮系统，包括第一压缩机和第二压缩机的压缩机部分以及涡轮部分。 涡轮机部分包括联接以驱动第一线轴的第一涡轮机，该第一涡轮机在第一轴向位置处联接到联接以驱动第一压缩机的压缩机毂。 第一卷轴还在第二轴向位置处耦合到风扇驱动输入轴，该风扇驱动输入轴联接以驱动风扇驱动齿轮系统。 第二涡轮通过第二阀芯联接以驱动第二压缩机。 速度传感器探头可操作以确定第一卷轴的旋转速度。 速度传感器探头位于第一轴向位置和第二轴向位置的轴向后方。

    REMOTE SHAFT DRIVEN OPEN ROTOR PROPULSION SYSTEM WITH ELECTRICAL POWER GENERATION
    8.
    发明申请
    REMOTE SHAFT DRIVEN OPEN ROTOR PROPULSION SYSTEM WITH ELECTRICAL POWER GENERATION 有权
    带有电力发电的遥控开关转子推进系统

    公开(公告)号：US20120128487A1

    公开(公告)日：2012-05-24

    申请号：US12954161

    申请日：2010-11-24

    申请人： DAVID JOHN HOWARD EAMES

    发明人： DAVID JOHN HOWARD EAMES

    IPC分类号： F01D7/00

    CPC分类号： F01D15/10 ,  B64C11/346 ,  B64C11/48 ,  B64D27/14 ,  B64D35/06 ,  B64D41/00 ,  B64D2027/005 ,  B64D2033/0213 ,  F01D7/00 ,  F01D15/12 ,  F05D2220/325 ,  F05D2220/326 ,  Y02T50/66 ,  Y02T50/671 ,  Y02T50/673

    摘要： A system for aircraft propulsion is disclosed herein. The system includes a power plant. The system also includes an open rotor module operable to rotate. The open rotor module has a plurality of variable-pitch blades. The system also includes a first linkage extending between the power plant and the open rotor module. The first linkage is operable to transmit rotational power to the open rotor module for rotating the plurality of variable-pitch blades. The system also includes an actuator operable to change a pitch of the plurality of variable-pitch blades. The system also includes a generator operable to generate electric power. The system also includes a second linkage extending between the power plant and the generator. The second linkage is operable to transmit rotational power to the generator. The generator is operable to convert the rotational power to electrical power. The system also includes a controller operably coupled to the actuator to vary a pitch of the plurality of variable-pitch blades. The controller is also operably coupled to the power plant to adjust a power output. The controller is also operably coupled to the generator to determine demand on the generator. The controller is also operable to vary the pitch of the plurality of variable-pitch blades based at least in part on the demand on the generator.

    摘要翻译： 本文公开了一种用于飞行器推进的系统。 该系统包括发电厂。 该系统还包括可操作以旋转的开放转子模块。 开式转子模块具有多个可变桨距叶片。 该系统还包括在发电厂和开放式转子模块之间延伸的第一连杆。 第一联动装置可操作地将旋转动力传递到开式转子模块，以旋转多个可变桨距叶片。 该系统还包括可操作以改变多个可变桨距叶片的桨距的致动器。 该系统还包括可发电的发电机。 该系统还包括在发电厂和发电机之间延伸的第二连接。 第二连杆可操作以将旋转动力传递给发电机。 发电机可操作以将旋转功率转换成电力。 该系统还包括可操作地耦合到致动器以改变多个可变桨距叶片的桨距的控制器。 控制器还可操作地耦合到发电厂以调节功率输出。 控制器还可操作地耦合到发电机以确定对发电机的需求。 控制器还可操作以至少部分地基于对发电机的需求来改变多个可变桨距叶片的桨距。

    Gas turbine engine provided with a foreign matter removal passage
    10.
    发明授权
    Gas turbine engine provided with a foreign matter removal passage 有权
    具有异物去除通道的燃气轮机

    公开(公告)号：US07658061B2

    公开(公告)日：2010-02-09

    申请号：US10588600

    申请日：2005-08-31

    申请人： Osamu Kawamoto ,  Hiroki Nagata ,  Masayuki Fukutani ,  Mineyasu Oana

    发明人： Osamu Kawamoto ,  Hiroki Nagata ,  Masayuki Fukutani ,  Mineyasu Oana

    IPC分类号： F02C7/05

    CPC分类号： F02K3/06 ,  F02C7/05 ,  F02C7/052 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2250/323 ,  F05D2250/71 ,  F05D2260/607 ,  Y02T50/675

    摘要： To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air.The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

    摘要翻译： 提供结构简单但能有效地从燃烧空气中除去异物的燃气轮机。 进气通道21包括入口部分29，弯曲部分30和直径减小部分31.旁路管道24在对应于弯曲部分30的区域和相对于弯曲部分30的直径减小部分31的区域中弯曲离开中心轴线CL 进气通道29.在进气通道29和旁通管道24之间限定有一个环形空间32.在直径缩小部分31中，外衬套20形成有大量异物导入孔33， 进气通道21和环形空间32.内壳体4在其一部分中周向布置形成有多个异物排出孔34，其向外弯曲以在环形空间32和旁路管道24之间连通。