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148 条记录 (耗时 0.018 秒)

    Gas turbine engine compressor arrangement
    91.
    发明授权
    Gas turbine engine compressor arrangement 有权
    燃气涡轮发动机压缩机布置

    公开(公告)号：US08807477B2

    公开(公告)日：2014-08-19

    申请号：US13340969

    申请日：2011-12-30

    申请人： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

    发明人： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

    IPC分类号： B64D29/00

    CPC分类号： B64D27/26 ,  B64D2027/264 ,  B64D2027/266

    摘要： A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.

    摘要翻译： 燃气涡轮发动机包括风扇部分和包括低压压缩机部分的低阀芯。 低压压缩机部分包括八（8）个或更少的阶段。 高阀芯包括高压压缩机部分，其具有8至15（8-15）级。 整体压缩机压力比由低压压缩机部分和高压压缩机的组合提供。 齿轮系沿发动机中心线定义。 低阀芯可操作以通过齿轮系驱动风扇部分。

    GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION
    92.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION 审中-公开
    具有可靠性的GEARED TURBOFAN气动涡轮发动机检查齿轮连接

    公开(公告)号：US20140216053A1

    公开(公告)日：2014-08-07

    申请号：US13595155

    申请日：2012-08-27

    申请人： Michael E. McCune ,  Frederick M. Schwarz

    发明人： Michael E. McCune ,  Frederick M. Schwarz

    IPC分类号： F01D21/00

    CPC分类号： F01D21/003 ,  F02K3/06 ,  F05D2260/40311 ,  F05D2260/80 ,  F05D2270/021 ,  F05D2270/022

    摘要： A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a speed reduction. A sensor senses a speed of rotation of the fan and communicates sensed speed information to a control. The control develops an expected speed for the fan. A problem is identified should the sensed speed be less than the expected speed by more than a predetermined amount. A method is also described.

    摘要翻译： 燃气涡轮发动机包括风扇和压缩机。 燃烧器驱动涡轮机，包括具有轴的第一涡轮机以驱动压缩机。 风扇驱动器涡轮机通过减速来驱动风扇。 传感器感测风扇的旋转速度并将感测的速度信息传送到控制器。 控制开发出风扇的预期速度。 如果感测的速度小于预期速度超过预定量，则识别出问题。 还描述了一种方法。

    Epicyclic gear train
    93.
    发明授权
    Epicyclic gear train 有权
    行星齿轮系

    公开(公告)号：US08708863B2

    公开(公告)日：2014-04-29

    申请号：US13340735

    申请日：2011-12-30

    申请人： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

    发明人： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

    IPC分类号： F16H57/04

    CPC分类号： F01D5/027 ,  F02C7/32 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0479 ,  F16H57/0486 ,  F16H2057/085

    摘要： An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. Each journal bearing includes an internal central cavity and at least one passage that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3.

    摘要翻译： 行星齿轮系包括支撑与太阳齿轮啮合的星形齿轮的载体。 环形齿轮围绕并与星形齿轮啮合。 每个星形齿轮都支撑在相应的轴颈轴承上。 每个轴颈轴承包括内部中心腔和至少一个从内腔径向延伸到相应轴颈轴承的周向轴颈表面的通道。 行星齿轮系具有大于或等于约2.3的齿轮减速比。

    GEARED ARCHITECTURE WITH INDUCER FOR GAS TURBINE ENGINE
    95.
    发明申请
    GEARED ARCHITECTURE WITH INDUCER FOR GAS TURBINE ENGINE 有权
    具有用于气体涡轮发动机的电动机的齿轮架构

    公开(公告)号：US20130259652A1

    公开(公告)日：2013-10-03

    申请号：US13437395

    申请日：2012-04-02

    申请人： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    发明人： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    IPC分类号： F01D15/12

    CPC分类号： F02C7/36 ,  F02K3/06 ,  F05D2260/40311

    摘要： A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train.

    摘要翻译： 燃气涡轮发动机包括围绕公共轴线旋转的第一和第二轴。 第一涡轮部分被支撑在第一轴上。 第二压缩机和涡轮机部分被支撑在第二轴上。 燃气涡轮发动机包括风扇。 第一压缩机部分与第二压缩机和第一和第二涡轮机以轴向流动关系布置。 齿轮架构可操作地连接第一轴和风扇。 诱导器操作耦合到齿轮系。

    GEARED TURBOFAN ENGINE WITH COUNTER-ROTATING SHAFTS
    98.
    发明申请
    GEARED TURBOFAN ENGINE WITH COUNTER-ROTATING SHAFTS 审中-公开
    具有反转运动的齿轮涡轮发动机

    公开(公告)号：US20130192256A1

    公开(公告)日：2013-08-01

    申请号：US13365288

    申请日：2012-02-03

    申请人： Gabriel L. Suciu ,  Frederick M. Schwarz

    发明人： Gabriel L. Suciu ,  Frederick M. Schwarz

    IPC分类号： F02C7/20 ,  F02C3/04

    CPC分类号： F01D25/162 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06 ,  F02K3/072 ,  Y02T50/671

    摘要： A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. The mid-turbine frame carries a plurality of vanes to redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine. In another feature, a power density is defined as the thrust divided by the volume of a turbine section, and the power density is of about 1.5 lbf per in3.

    摘要翻译： 中间涡轮机框架结合到高压涡轮机和低压涡轮机中间的燃气涡轮发动机的涡轮机部分中。 高压和低压涡轮机在相反方向旋转。 中间涡轮机框架承载多个叶片，以在高压涡轮机接近低压涡轮机时重新定向流向下游的流。 在另一个特征中，功率密度被定义为推力除以涡轮机部分的体积，并且功率密度约为每磅1/3磅。

    GEARED TURBOFAN WITH DISTRIBUTED ACCESSORY GEARBOXES
    100.
    发明申请
    GEARED TURBOFAN WITH DISTRIBUTED ACCESSORY GEARBOXES 审中-公开
    具有分布式附件齿轮的齿轮涡轮机

    公开(公告)号：US20130125561A1

    公开(公告)日：2013-05-23

    申请号：US13459783

    申请日：2012-04-30

    申请人： Frederick M. Schwarz ,  Michael Winter

    发明人： Frederick M. Schwarz ,  Michael Winter

    IPC分类号： F02C6/00

    CPC分类号： F02C6/00 ,  F01D7/02 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/4031

    摘要： A disclosed gas turbine engine includes a core engine defined about an engine centerline axis, the core engine including a compressor section driven through a shaft by a turbine section. A core nacelle surrounds the core engine and a fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path for a bypass airflow. A fan section disposed within the fan nacelle is driven by the turbine section of the core engine through a geared architecture. An engine pylon supports the core nacelle and the fan nacelle. A towershaft is driven by the shaft of the core engine and drives a generator mounted within the core nacelle. The generator powers an electric motor mounted within the engine pylon. The electric motor drives a plurality of accessory components that are also mounted within the engine pylon.

    摘要翻译： 所公开的燃气涡轮发动机包括围绕发动机中心线轴线限定的核心发动机，所述核心发动机包括通过涡轮部分驱动穿过轴的压缩机部分。 核心机舱围绕核心发动机，并且风扇机舱至少部分地安装在核心机舱周围以限定用于旁路气流的风扇旁路流动路径。 设置在风扇机舱内的风扇部分通过齿轮架构由核心发动机的涡轮机部分驱动。 发动机塔架支撑核心机舱和风扇机舱。 塔轴由核心发动机的轴驱动并驱动安装在核心机舱内的发电机。 发电机为安装在发动机塔架内的电动机供电。 电动机驱动也安装在发动机塔架内的多个附件部件。