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1799 条记录 (耗时 0.023 秒)

    Direct drive rotation device for passively moving fluid
    1.
    发明授权
    Direct drive rotation device for passively moving fluid 有权
    直接驱动旋转装置，用于被动移动流体

    公开(公告)号：US09541188B2

    公开(公告)日：2017-01-10

    申请号：US14532142

    申请日：2014-11-04

    申请人： Bell Helicopter Textron Inc. ,  Bell Helicopter Textron Inc.

    发明人： Eric A. Sinusas ,  Walter West Riley

    IPC分类号： F16H57/04 ,  B64C27/12 ,  F16N7/18 ,  F16H1/14

    CPC分类号： F16H57/0409 ,  B64C27/12 ,  F16H1/14 ,  F16H57/0427 ,  F16H57/0428 ,  F16H57/0436 ,  F16H57/0443 ,  F16H57/0471 ,  F16H57/0495 ,  F16N7/18 ,  Y10T74/19991

    摘要： The device is configured for moving a fluid within a gearbox. In one illustrative embodiment, the device includes a base portion coupled to a rotatable member within the gearbox. An inlet portion of the device is configured to draw the fluid from a reservoir portion of the gearbox. The device is configured to utilize a centrifugal force for moving the fluid from the inlet portion toward the base portion along an interior surface of a conical portion. In another illustrative embodiment, the device includes a conical portion having an external threaded portion configured to capture a fluid during a rotation of the device. In such an embodiment, the threaded portion is configured to utilize a centrifugal force for moving the fluid captured by the threaded portion along an exterior surface of the conical portion.

    摘要翻译： 该装置被配置为移动齿轮箱内的流体。 在一个说明性实施例中，该装置包括联接到齿轮箱内的可旋转构件的基部。 装置的入口部分构造成从齿轮箱的储存部分抽取流体。 该装置构造成利用离心力沿着锥形部分的内表面将流体从入口部分移向基部。 在另一示例性实施例中，该装置包括锥形部分，其具有被配置为在装置旋转期间捕获流体的外部螺纹部分。 在这种实施例中，螺纹部分构造成利用离心力来沿着锥形部分的外表面移动由螺纹部分捕获的流体。

    DIRECT DRIVE ROTATION DEVICE FOR PASSIVELY MOVING FLUID
    2.
    发明申请
    DIRECT DRIVE ROTATION DEVICE FOR PASSIVELY MOVING FLUID 有权
    直接驱动旋转装置，用于无源移动流体

    公开(公告)号：US20150211544A1

    公开(公告)日：2015-07-30

    申请号：US14679473

    申请日：2015-04-06

    申请人： Bell Helicopter Textron Inc. ,  Bell Helicopter Textron Inc.

    发明人： Eric A. Sinuses ,  Walter West Riley

    IPC分类号： F04D29/38 ,  F16H1/14

    CPC分类号： F04D29/384 ,  B64C27/12 ,  F16H1/14 ,  F16H57/0427 ,  F16H57/0428 ,  F16H57/0471 ,  F16H57/0495 ,  F16N7/18 ,  F16N7/363 ,  Y10T74/19991

    摘要： The device is configured for moving a fluid within a gearbox. In one illustrative embodiment, the device includes a base portion coupled to a rotatable member within the gearbox. An inlet portion of the device is configured to draw the fluid from a reservoir portion of the gearbox. The device is configured to utilize a centrifugal force for moving the fluid from the inlet portion toward the base portion along an interior surface of a conical portion. In another illustrative embodiment, the device includes a conical portion having an external threaded portion configured to capture a fluid during a rotation of the device. In such an embodiment, the threaded portion is configured to utilize a centrifugal force for moving the fluid captured by the threaded portion along an exterior surface of the conical portion.

    摘要翻译： 该装置被配置为移动齿轮箱内的流体。 在一个说明性实施例中，该装置包括联接到齿轮箱内的可旋转构件的基部。 装置的入口部分构造成从齿轮箱的储存部分抽取流体。 该装置构造成利用离心力沿着锥形部分的内表面将流体从入口部分移向基部。 在另一示例性实施例中，该装置包括锥形部分，其具有被配置为在装置旋转期间捕获流体的外部螺纹部分。 在这种实施例中，螺纹部分构造成利用离心力来沿着锥形部分的外表面移动由螺纹部分捕获的流体。

    Aircraft landing-gear step
    4.
    外观设计
    Aircraft landing-gear step 有权

    公开(公告)号：USD1009762S1

    公开(公告)日：2024-01-02

    申请号：US29675592

    申请日：2019-01-03

    申请人： Bell Helicopter Textron Inc.

    设计人： Paul Charles Griffiths ,  Steven Loveland ,  Allen Brittain

    摘要： FIG. 1 a bottom perspective view of the aircraft landing-gear step.
    FIG. 2 is a front elevational view of the landing-gear step as configured in FIG. 1.
    FIG. 3 is a rear elevational view of the landing-gear step as configured in FIG. 1.
    FIG. 4 is a left side elevational view of the landing-gear step as configured in FIG. 1.
    FIG. 5 is a right side elevational view of the landing-gear step as configured in FIG. 1.
    FIG. 6 is a top plan view of the landing-gear step as configured in FIG. 1.
    FIG. 7 is a bottom plan view of the landing-gear step as configured in FIG. 1.
    FIG. 8 is a top perspective view of the aircraft landing-gear step shown in an environment of use.
    FIG. 9 is an oblique view of the left landing-gear step, the door being configured in a closed position.
    FIG. 10 is a front elevational view of the landing-gear step as configured in FIG. 9.
    FIG. 11 is a rear elevational view of the landing-gear step as configured in FIG. 9.
    FIG. 12 is a left side elevational view of the landing-gear step as configured FIG. 9.
    FIG. 13 is a right side elevational view of the landing-gear step as configured in FIG. 9.
    FIG. 14 is a top plan view of the landing-gear step as configured in FIG. 9.
    FIG. 15 is a bottom plan view of the landing-gear step as configured in FIG. 9; and,
    FIG. 16 is an oblique view of the landing-gear step as configured in FIG. 9.
    The broken lines shown in FIGS. 1-7 and 9-15 illustrate portions of the aircraft landing-gear step that form no part of the claimed design; the additional broken lines shown in FIGS. 8 and 16 are for purposes of illustrating environmental subject matter only and forms no part thereof. The right side not shown is understood to be a mirror image of the left side shown in FIGS. 1-8 and 9-16.

    Reduced height swashplate assembly
    9.
    发明授权
    Reduced height swashplate assembly 有权

    公开(公告)号：US11643197B2

    公开(公告)日：2023-05-09

    申请号：US16210489

    申请日：2018-12-05

    申请人： Bell Helicopter Textron Inc.

    发明人： Scott David Poster ,  Charles Hubert Speller ,  Mark Adam Wiinikka

    IPC分类号： B64C27/605 ,  F01D5/02

    CPC分类号： B64C27/605 ,  F01D5/02

    摘要： A swashplate assembly includes: a mounting sleeve configured for coupling to and around an upper portion of a gearbox, wherein the mounting sleeve extends downwards from the upper portion of the gearbox; a tilt sleeve coupled to the mounting sleeve, wherein the tilt sleeve has a curved exterior surface; a non-rotating swashplate ring positioned around the tilt sleeve, wherein the non-rotating swashplate ring has a first set of pitch control connectors and an anti-rotation connector; a rotating swashplate ring rotatable about the non-rotating swashplate ring, wherein the rotating swashplate ring has a second set of pitch control connectors and a drive link connector; and a first bearing system mounted between the non-rotating swashplate ring and the rotating swashplate ring.