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17 条记录 (耗时 0.023 秒)

    Air turbine starter with unitary inlet and stator
    1.
    发明申请
    Air turbine starter with unitary inlet and stator 有权
    具有整体入口和定子的空气涡轮起动器

    公开(公告)号：US20050058542A1

    公开(公告)日：2005-03-17

    申请号：US10661312

    申请日：2003-09-12

    申请人： Roy Kruegel ,  Cynthia Byers ,  Gary Armstrong ,  Todd Langston ,  Marvin Collins

    发明人： Roy Kruegel ,  Cynthia Byers ,  Gary Armstrong ,  Todd Langston ,  Marvin Collins

    IPC分类号： F01D1/02

    CPC分类号： F02C7/277 ,  Y02T50/671 ,  Y10T29/4932

    摘要： An air turbine starter for use in aircraft or other gas turbine engine applications. In a particular embodiment, the air turbine starter has a titanium unitary inlet structure. The unitary inlet structure has a housing having a longitudinal centerline. The housing defines an air inlet, a mounting surface, and a flow path therebetween. Integrally formed inside the housing and transverse to the longitudinal centerline is a stator for directing the flow of air in to the turbine blades of the turbine starter. The stator has a central circular body with a plurality of angularly spaced circumferentially mounted stator fins. An improved unitary inlet structure and method for making such a unitary inlet and stator are also provided.

    摘要翻译： 用于飞机或其他燃气涡轮发动机应用的空气涡轮起动器。 在特定实施例中，空气涡轮起动器具有钛单一入口结构。 整体入口结构具有纵向中心线的壳体。 壳体限定空气入口，安装表面和它们之间的流动路径。 整体地形成在壳体内部并且横向于纵向中心线的是用于将空气流引导到涡轮启动器的涡轮机叶片的定子。 定子具有中心圆形体，其具有多个角度间隔开的周向安装的定子翅片。 还提供了改进的单一入口结构和制造这种单一入口和定子的方法。

    Aircraft engine accessory drive air film riding bulkhead seal
    3.
    发明申请
    Aircraft engine accessory drive air film riding bulkhead seal 审中-公开
    飞机发动机附件驱动空气膜乘坐舱壁密封

    公开(公告)号：US20060207834A1

    公开(公告)日：2006-09-21

    申请号：US11072840

    申请日：2005-03-03

    申请人： William Giesler ,  Todd Langston ,  Jennifer Zonneveld ,  David Mathis ,  Cynthia Byers

    发明人： William Giesler ,  Todd Langston ,  Jennifer Zonneveld ,  David Mathis ,  Cynthia Byers

    IPC分类号： F16N7/02

    CPC分类号： F02C7/32 ,  F01D11/04 ,  F01D25/183

    摘要： The present invention provides a lubrication system for supplying lubricant between a first housing and a second housing, where the first and second housings each comprising air and lubricant. In one exemplary embodiment, the system includes a lubricant supply tube, an output shaft, and a seal assembly. The lubricant supply tube extends at least partially through the second housing and is configured to receive a supply of lubricant from the first housing. The output shaft is rotationally mounted within the second housing. The seal assembly is mounted on the output shaft and disposed within the second housing. The seal assembly is configured to pump at least a portion of the air out of the second housing.

    摘要翻译： 本发明提供一种用于在第一壳体和第二壳体之间供应润滑剂的润滑系统，其中第一和第二壳体各自包括空气和润滑剂。 在一个示例性实施例中，系统包括润滑剂供应管，输出轴和密封组件。 润滑剂供应管至少部分地延伸穿过第二壳体并且构造成从第一壳体接收润滑剂供应。 输出轴旋转地安装在第二壳体内。 密封组件安装在输出轴上并且设置在第二壳体内。 密封组件构造成将至少一部分空气泵出第二壳体。

    Aircraft electric taxi system with friction actuated, bi-directional clutch
    4.
    发明授权
    Aircraft electric taxi system with friction actuated, bi-directional clutch 有权
    具有摩擦致动，双向离合器的飞机电动出租车系统

    公开(公告)号：US08617019B2

    公开(公告)日：2013-12-31

    申请号：US12950874

    申请日：2010-11-19

    申请人： Donald J. Christensen ,  Todd Langston ,  David Lane Charles ,  Rudy Velasquez

    发明人： Donald J. Christensen ,  Todd Langston ,  David Lane Charles ,  Rudy Velasquez

    IPC分类号： F16H48/06

    CPC分类号： B64C25/405 ,  F16D41/125 ,  Y02T50/823

    摘要： An electric taxi system (ETS) for an aircraft may comprise drive motors mounted coaxially with wheels of the aircraft. A clutch assembly may be interposed between the drive motor the wheel. The clutch assembly may transmit torque from the motor to the wheel when the wheel and a rotor of the motor rotate at the same rotational speed. The clutch assembly may self-disengage a rotor of the motor from the wheel when the wheel rotates faster than the rotor.

    摘要翻译： 用于飞机的电动出租车系统（ETS）可以包括与飞机的车轮同轴安装的驱动马达。 离合器组件可以介于驱动马达轮之间。 当车轮和电机的转子以相同的转速旋转时，离合器组件可以将扭矩从电动机传递到车轮。 当轮子转动比转子更快时，离合器组件可以使电动机的转子与车轮脱离接合。

    Low profile valve actuator having high torque output
    5.
    发明授权
    Low profile valve actuator having high torque output 失效
    具有高转矩输出的低调阀门执行器

    公开(公告)号：US08191860B2

    公开(公告)日：2012-06-05

    申请号：US12183886

    申请日：2008-07-31

    申请人： David M. Eschborn ,  Glenn H. Lane ,  Louie T. Gaines ,  Todd Langston

    发明人： David M. Eschborn ,  Glenn H. Lane ,  Louie T. Gaines ,  Todd Langston

    IPC分类号： F16K31/44

    CPC分类号： F16K31/54 ,  F16K31/043

    摘要： A valve actuator is provided for use in conjunction with a drive motor and a valve. In one embodiment, the valve actuator includes a housing assembly, a first power screw rotatably mounted in the housing assembly and configured to be rotated by the drive motor, a first rack translatably mounted in the housing assembly, and a pinion rotatably mounted in the housing assembly and mechanically linked to the valve. The first rack is threadably coupled to the first power screw and is configured to move linearly as the first power screw rotates. The pinion engages the first rack and is configured to rotate as the first rack moves linearly to move the valve to a desired position.

    摘要翻译： 提供一个与驱动马达和阀门一起使用的阀门致动器。 在一个实施例中，阀致动器包括壳体组件，可旋转地安装在壳体组件中并构造成由驱动电机旋转的第一动力螺杆，可平移地安装在壳体组件中的第一齿条和可旋转地安装在壳体中的小齿轮 组装并机械连接到阀门。 第一机架螺纹连接到第一动力螺杆，并被配置成随着第一动力螺杆旋转而线性运动。 小齿轮接合第一齿条并且构造成随着第一齿条线性移动以将阀移动到期望位置而旋转。

    Turbine drive system with lock-up clutch and method
    6.
    发明授权
    Turbine drive system with lock-up clutch and method 有权
    具有锁止离合器和方法的涡轮驱动系统

    公开(公告)号：US08146370B2

    公开(公告)日：2012-04-03

    申请号：US12124362

    申请日：2008-05-21

    申请人： Peter Kenneth Zeiner ,  Tony Libera ,  Todd Langston

    发明人： Peter Kenneth Zeiner ,  Tony Libera ,  Todd Langston

    IPC分类号： F02C3/10 ,  F02C6/00

    CPC分类号： F02C3/10 ,  F02C7/32 ,  F02C9/18 ,  Y02T50/671

    摘要： A pneumatically driven turbine drive system is coupled to a gas turbine engine that includes low and high pressure compressors, low and high pressure turbines, a lock-up clutch, and at least one engine accessory driven by the high pressure compressor. The pneumatically driven turbine drive system selectively bleeds air discharged from the high pressure compressor and supplies it to an air turbine that is coupled to the at least one engine accessory. Thus, the system selectively reduces the power extracted from the high pressure compressor and is capable of supplying power back to the engine core. This, coupled with the bleed air that is diverted from the high pressure turbine and the low pressure turbine, allows the high pressure spool and the low pressure spool to run at lower speeds when high engine thrust is not needed or desired, but when the at least one engine accessory is still needed.

    摘要翻译： 气动涡轮机驱动系统耦合到包括低压和高压压缩机，低压和高压涡轮机，锁止离合器和由高压压缩机驱动的至少一个发动机附件的燃气涡轮发动机。 气动驱动的涡轮驱动系统选择性地将从高压压缩机排出的空气排出并将其提供到联接到至少一个发动机附件的空气涡轮机。 因此，系统选择性地降低从高压压缩机提取的功率，并且能够将功率返回到发动机芯。 这与从高压涡轮机和低压涡轮机转向的排出空气相结合，允许高压阀芯和低压阀芯在不需要或期望的高发动机推力时以较低的速度运行，但是当at 仍然需要至少一个发动机附件。

    Air turbine starter assembly
    8.
    发明申请
    Air turbine starter assembly 失效
    空气涡轮起动器总成

    公开(公告)号：US20050167227A1

    公开(公告)日：2005-08-04

    申请号：US10769099

    申请日：2004-01-29

    申请人： Todd Langston

    发明人： Todd Langston

    IPC分类号： F16D11/00 ,  F16D41/12

    CPC分类号： F16D41/125

    摘要： An aircraft engine starter assembly has a starter motor, a notch containing plate rotationally coupled to the starter motor or the aircraft engine, a strut pocket containing plate rotationally coupled to the other of the starter motor or the aircraft engine, arranged facing the notch containing plate and spaced apart therefrom by an inter-plate space, wherein the strut pocket containing plate has a spring loaded strut mounted in at least one pocket thereof, aligned to engage a notch as the two plates rotate with respect to each other about a common centerline, so that the strut engages the notch to start the engine and releases from the notch when the engine is running. A lube oil pump is provided to force oil into the inter-plate space and bearings are provided coupled to the two plates to react the expansion forces created by the pressurized lube oil.

    摘要翻译： 飞机发动机起动器组件具有起动马达，与起动马达或飞行器发动机旋转地连接的凹口容纳板，支承托盘容纳板，旋转地连接到起动马达或飞机发动机中的另一个，布置成面向切口容纳板 并且通过板间空间与其间隔开，其中支柱袋容纳板具有安装在其至少一个凹部中的弹簧加载的支柱，当两个板围绕共同的中心线相对于彼此旋转时，所述支撑件对准以接合凹口， 使得支柱接合凹口以起动发动机并且在发动机运行时从凹口释放。 提供润滑油泵以迫使油进入板间空间，并且提供联接到两个板的轴承以对由加压润滑油产生的膨胀力作出反应。

    LOW PROFILE VALVE ACTUATOR HAVING HIGH TORQUE OUTPUT
    10.
    发明申请
    LOW PROFILE VALVE ACTUATOR HAVING HIGH TORQUE OUTPUT 失效
    具有高扭矩输出的低剖面阀执行器

    公开(公告)号：US20100025610A1

    公开(公告)日：2010-02-04

    申请号：US12183886

    申请日：2008-07-31

    申请人： David M. Eschborn ,  Glenn H. Lane ,  Louie T. Gaines ,  Todd Langston

    发明人： David M. Eschborn ,  Glenn H. Lane ,  Louie T. Gaines ,  Todd Langston

    IPC分类号： F16K31/44

    CPC分类号： F16K31/54 ,  F16K31/043

    摘要： A valve actuator is provided for use in conjunction with a drive motor and a valve. In one embodiment, the valve actuator includes a housing assembly, a first power screw rotatably mounted in the housing assembly and configured to be rotated by the drive motor, a first rack translatably mounted in the housing assembly, and a pinion rotatably mounted in the housing assembly and mechanically linked to the valve. The first rack is threadably coupled to the first power screw and is configured to move linearly as the first power screw rotates. The pinion engages the first rack and is configured to rotate as the first rack moves linearly to move the valve to a desired position.

    摘要翻译： 提供一个与驱动马达和阀门一起使用的阀门致动器。 在一个实施例中，阀致动器包括壳体组件，可旋转地安装在壳体组件中并构造成由驱动电机旋转的第一动力螺杆，可平移地安装在壳体组件中的第一齿条和可旋转地安装在壳体中的小齿轮 组装并机械连接到阀门。 第一机架螺纹连接到第一动力螺钉，并被配置成随着第一动力螺杆旋转而线性运动。 小齿轮接合第一齿条并且构造成随着第一齿条线性移动以将阀移动到期望位置而旋转。