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21 条记录 (耗时 0.021 秒)

    AIRCRAFT EMERGENCY POWER SYSTEM
    1.
    发明申请
    AIRCRAFT EMERGENCY POWER SYSTEM 审中-公开
    飞机紧急动力系统

    公开(公告)号：US20130076120A1

    公开(公告)日：2013-03-28

    申请号：US13036968

    申请日：2011-02-28

    申请人： Carl A. Wagner ,  Michael Krenz ,  David L. Jacques

    发明人： Carl A. Wagner ,  Michael Krenz ,  David L. Jacques

    IPC分类号： B64D33/00

    CPC分类号： B64D33/00 ,  B64D2221/00 ,  F01D15/10 ,  F05D2270/09

    摘要： An emergency power system for use on an aircraft includes an emergency electrical generator coupled to a mechanical power source for generating emergency electrical power. An electrical power distribution network connects the emergency electrical generator to a plurality of electrical loads. A controller controls the electrical power distribution network to selectively couple and decouple the electrical loads to and from the emergency electrical generator based upon a priority rank assigned to each of the electrical loads.

    摘要翻译： 用于飞行器的应急电力系统包括耦合到用于产生应急电力的机械电源的紧急发电机。 电力分配网络将紧急发电机连接到多个电负载。 控制器控制配电网络，以便基于分配给每个电负载的优先等级来选择性地将电力负载耦合到紧急发电机和从紧急发电机分离。

    LOW PRESSURE SPOOL EMERGENCY GENERATOR
    3.
    发明申请
    LOW PRESSURE SPOOL EMERGENCY GENERATOR 审中-公开
    低压SPOOL应急发电机

    公开(公告)号：US20120221157A1

    公开(公告)日：2012-08-30

    申请号：US13036994

    申请日：2011-02-28

    申请人： Adam M. Finney ,  Michael Krenz ,  Carl A. Wagner ,  David L. Jacques

    发明人： Adam M. Finney ,  Michael Krenz ,  Carl A. Wagner ,  David L. Jacques

    IPC分类号： B60L1/00 ,  G06F1/26

    CPC分类号： G06F1/26 ,  B64D41/00 ,  B64D2221/00 ,  F01D15/10 ,  F02C7/32 ,  F05D2270/09 ,  Y02T50/53

    摘要： An emergency power system is useable on an aircraft having a gas turbine engine with a low pressure spool and a high pressure spool. The emergency power system includes an emergency electrical generator coupled to the low pressure spool during an emergency for generating emergency electrical power and one or more additional electrical power sources. A plurality of electrical loads are electrically connected to the emergency electrical generator and the one or more additional electrical power sources. Aircraft sensors provide data regarding emergency electrical power availability and emergency electrical power demand. A controller for controlling the emergency electrical generator determines emergency electrical power demand and emergency electrical power availability based upon data from the aircraft sensors. The controller controls the emergency electrical generator based upon the emergency electrical power demand and the emergency electrical power availability.

    摘要翻译： 应急电力系统可用于具有带有低压阀芯和高压阀芯的燃气涡轮发动机的飞机上。 应急电力系统包括在紧急情况期间联接到低压阀芯的紧急发电机，用于产生紧急电力和一个或多个附加电力源。 多个电负载电连接到紧急发电机和一个或多个附加电源。 飞机传感器提供有关应急电力可用性和应急电力需求的数据。 用于控制紧急发电机的控制器基于来自飞行器传感器的数据来确定应急电力需求和应急电力可用性。 控制器根据紧急电力需求和应急电力可用性控制应急发电机。

    Dual impeller pump
    6.
    发明授权
    Dual impeller pump 失效
    双叶轮泵

    公开(公告)号：US4732236A

    公开(公告)日：1988-03-22

    申请号：US852773

    申请日：1986-04-16

    申请人： David L. Jacques

    发明人： David L. Jacques

    IPC分类号： F04D29/22 ,  F04D1/00 ,  F04D29/06 ,  F01M11/06

    CPC分类号： F04D29/06 ,  F04D1/006

    摘要： A liquid scavenging pump system for scavenging oil or the like from a blower, an engine or the like. A casing is provided for housing the blower and defining an oil receiving cavity. A dual pump is mounted in the casing and has first and second pumps in communication with the casing cavity for conjoint rotation. A first inlet is provided from the casing cavity to the first pump, and a first outlet is provided from the first pump for delivering oil from the cavity to a pump or the like. A second inlet is provided from the casing cavity, remote from the first inlet, to the second pump. The second outlet from the second pump is in communication with the first inlet to the first pump to facilitate operating the pump at various attitudes. The dual pump is of the radial-vaned impeller type, but includes two sets of axially spaced impeller vanes separated by a common barrier and including a sleeve for mounting on a common drive shaft. The impeller vanes, the barrier and the sleeve all are fabricated as a single unitarily constructed structure, such as by molding.

    摘要翻译： 一种用于从鼓风机，发动机等中清除油等的液体清除泵系统。 提供了用于容纳鼓风机并限定油接收腔的壳体。 双泵安装在壳体中，并且具有与壳体腔连通的第一和第二泵，用于联合旋转。 从壳体腔向第一泵提供第一入口，并且从第一泵提供第一出口，用于将油从空腔输送到泵等。 第二入口从壳体空腔提供，远离第一入口到第二泵。 来自第二泵的第二出口与第一泵的第一入口连通，以便以各种姿态操作泵。 双泵是径向叶轮类型的，但是包括两组轴向隔开的叶轮叶片，它们由公共挡板分开并且包括用于安装在公共驱动轴上的套筒。 叶轮叶片，阻挡件和套筒都被制造为单一的整体结构，例如通过模制。

    FLYWEIGHT FOR RAM AIR TURBINE
    10.
    发明申请
    FLYWEIGHT FOR RAM AIR TURBINE 有权
    飞行员空气涡轮机

    公开(公告)号：US20130230401A1

    公开(公告)日：2013-09-05

    申请号：US13410351

    申请日：2012-03-02

    申请人： David G. Bannon ,  David L. Jacques

    发明人： David G. Bannon ,  David L. Jacques

    IPC分类号： F01D7/02 ,  F01D1/20 ,  B23P17/00 ,  F01D7/00

    CPC分类号： F01D7/02 ,  B64D41/007 ,  Y10T29/49229

    摘要： A flyweight for use in a ram air turbine has a body with a circumferentially enlarged portion extending between flat sides spaced by an angle of between 45 degrees and 150 degrees. A pivot point is defined by a bore at a circumferentially intermediate point in the body, and in a relatively thin inner portion. The relatively thin inner portion extends beyond the pivot point to an end that will be radially inward when the flyweight is mounted in a ram air turbine. A governor, a ram air turbine and a method are also described.

    摘要翻译： 用于冲压式空气涡轮机的飞重物具有主体，该主体具有在间隔45度至150度之间的平面之间延伸的周向扩大部分。 枢轴点由身体中的周向中间点处的孔和相对薄的内部部分限定。 相对较薄的内部部分延伸超过枢转点到当飞轮重量安装在压头空气涡轮机时将径向向内的端部。 还描述了调速器，冲压空气涡轮机和方法。