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公开(公告)号：US10378978B2
公开(公告)日：2019-08-13
申请号：US15807958
申请日：2017-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Ryan T. Ehinger , David R. Bockmiller
Abstract: A method for calculating torque through a rotor mast of a propulsion system of a tiltrotor aircraft includes receiving the torque being applied through a quill shaft of the rotorcraft. The quill shaft is located between a fixed gearbox and a spindle gearbox, and the spindle gearbox is rotatable about a conversion access. The torque through the rotor mast is determined by using the torque through the quill shaft and the efficiency loss value between the quill shaft and the rotor mast.
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公开(公告)号：US09834303B2
公开(公告)日：2017-12-05
申请号：US13966726
申请日：2013-08-14
Applicant: Bell Helicopter Textron Inc.
Inventor： David R. Bockmiller , James E. Kooiman
CPC classification number: B64C27/22 , B64C29/0033 , B64F5/40 , Y10T29/49318 , Y10T74/1966
Abstract: A quill shaft is configured for transferring torque and accepting misalignments between a fixed gearbox and a rotatable spindle gearbox in a propulsion system of a tiltrotor aircraft, the quill shaft includes a first splined portion configured for coupling to an output gear of the fixed gearbox, and a second splined portion configured for coupling to an input gear of the spindle gearbox. The spindle gearbox includes a rotor mast associated therewith, the spindle gearbox being rotatable so that the tiltrotor aircraft can selectively operate in a helicopter mode and airplane mode.
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公开(公告)号：US10816085B2
公开(公告)日：2020-10-27
申请号：US15874054
申请日：2018-01-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric S. Olson , David R. Bockmiller
Abstract: A system is provided in one example embodiment and may include a first reservoir for a lubricant; a second reservoir for the lubricant, wherein the first reservoir and the second reservoir are interconnected; a first pumping element to pump the lubricant from the first reservoir at a first flow rate; a second pumping element to pump the lubricant at a second flow rate, wherein the first flow rate and the second flow rate are different; and a gearbox coupled to the first pumping element and the second pumping element. The first reservoir may have a larger volume than the second reservoir and the first flow rate may be higher than the second flow rate.
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公开(公告)号：US09663225B1
公开(公告)日：2017-05-30
申请号：US15417113
申请日：2017-01-26
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , George Ryan Decker , Andrew G. Baines , David R. Bockmiller , Erick Wayne Kohler
CPC classification number: B64C29/0033 , B64C27/22 , B64D35/00 , B64F5/40 , F16H1/006 , Y10T29/49318 , Y10T74/1966
Abstract: A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.
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5.发明申请METHOD AND APPARATUS OF CONNECTING A FIXED DRIVE SYSTEM TO A ROTATING DRIVE SYSTEM FOR A TILTROTOR AIRCRAFT 有权将固定的驱动系统连接到旋转飞行器的旋转驱动系统的方法和装置公开(公告)号：US20150048214A1
公开(公告)日：2015-02-19
申请号：US13966726
申请日：2013-08-14
Applicant: Bell Helicopter Textron Inc.
Inventor： David R. Bockmiller , James E. Kooiman
CPC classification number: B64C27/22 , B64C29/0033 , B64F5/40 , Y10T29/49318 , Y10T74/1966
Abstract: A quill shaft is configured for transferring torque and accepting misalignments between a fixed gearbox and a rotatable spindle gearbox in a propulsion system of a tiltrotor aircraft, the quill shaft includes a first splined portion configured for coupling to an output gear of the fixed gearbox, and a second splined portion configured for coupling to an input gear of the spindle gearbox. The spindle gearbox includes a rotor mast associated therewith, the spindle gearbox being rotatable so that the tiltrotor aircraft can selectively operate in a helicopter mode and airplane mode.
Abstract translation: 套筒轴构造成用于在倾斜旋翼飞行器的推进系统中传递扭矩并接收固定齿轮箱和可旋转主轴齿轮箱之间的不对准，所述轴卷轴包括构造成联接到固定齿轮箱的输出齿轮的第一花键部分，以及 第二花键部分，其构造成联接到主轴齿轮箱的输入齿轮。 主轴齿轮箱包括与其相关联的转子桅杆，主轴齿轮箱可旋转，使得倾斜旋翼飞机可以选择性地以直升机模式和飞行模式操作。
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Patent Agency Ranking
公开(公告)号：US20140263855A1
公开(公告)日：2014-09-18
申请号：US13801674
申请日：2013-03-13
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Brent C. Ross , David R. Bockmiller , Mark L. Isaac , Brian J. Cox
CPC classification number: B64C29/0033 , B64C27/26 , B64C29/0075
Abstract: A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed location on a wing member; a prop-rotor pylon mechanically coupled to the engine along a drive path, and a gearbox disposed in the drive path. The prop-rotor pylon is rotatably mounted on a spindle, and the prop-rotor pylon is configured to selectively rotate about a rotational axis of the spindle between a vertical position and a horizontal position. The gearbox comprises a rotational axis aligned with the rotational axis of the spindle.
Abstract translation: 用于倾斜转子飞行器的转子系统包括设置在翼构件上的第一固定位置处的发动机; 沿着驱动路径机械耦合到发动机的支柱转子塔架，以及设置在驱动路径中的齿轮箱。 支柱转子塔架可旋转地安装在主轴上，并且支柱转子塔架构造成围绕主轴的旋转轴线在垂直位置和水平位置之间选择性地旋转。 齿轮箱包括与主轴的旋转轴线对准的旋转轴线。
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公开(公告)号：US20190219149A1
公开(公告)日：2019-07-18
申请号：US15874054
申请日：2018-01-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric S. Olson , David R. Bockmiller
CPC classification number: F16H57/0442 , B64C27/04 , B64C27/32 , B64C29/0033 , B64C29/0091 , B64D35/00 , F16H57/0441 , F16H57/0449 , F16H57/045
Abstract: A system is provided in one example embodiment and may include a first reservoir for a lubricant; a second reservoir for the lubricant, wherein the first reservoir and the second reservoir are interconnected; a first pumping element to pump the lubricant from the first reservoir at a first flow rate; a second pumping element to pump the lubricant at a second flow rate, wherein the first flow rate and the second flow rate are different; and a gearbox coupled to the first pumping element and the second pumping element. The first reservoir may have a larger volume than the second reservoir and the first flow rate may be higher than the second flow rate.
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公开(公告)号：US20180067006A1
公开(公告)日：2018-03-08
申请号：US15807958
申请日：2017-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Ryan T. Ehinger , David R. Bockmiller
Abstract: A method for calculating torque through a rotor mast of a propulsion system of a tiltrotor aircraft includes receiving the torque being applied through a quill shaft of the rotorcraft. The quill shaft is located between a fixed gearbox and a spindle gearbox, and the spindle gearbox is rotatable about a conversion access. The torque through the rotor mast is determined by using the torque through the quill shaft and the efficiency loss value between the quill shaft and the rotor mast.
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公开(公告)号：US09841333B2
公开(公告)日：2017-12-12
申请号：US14526621
申请日：2014-10-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Ryan T. Ehinger , David R. Bockmiller
Abstract: A method for calculating torque through a rotor mast of a propulsion system of a tiltrotor aircraft includes receiving the torque being applied through a quill shaft of the rotorcraft. The quill shaft is located between a fixed gearbox and a spindle gearbox, and the spindle gearbox is rotatable about a conversion access. The torque through the rotor mast is determined by using the torque through the quill shaft and the efficiency loss value between the quill shaft and the rotor mast.
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公开(公告)号：US20170225780A1
公开(公告)日：2017-08-10
申请号：US15497055
申请日：2017-04-25
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , George Ryan Decker , Andrew G. Baines , David R. Bockmiller , Erick Wayne Kohler
CPC classification number: B64C29/0033 , B64C27/22 , B64D35/00 , B64F5/40 , F16H1/006 , Y10T29/49318 , Y10T74/1966
Abstract: A support assembly for coupling a first gearbox to an airframe of an aircraft. The first gearbox has an output gear operable to transfer torque to an input gear of a second gearbox via a common shaft rotatable about a longitudinal axis. The support assembly includes a fixed joint proximate the longitudinal axis. A first directional reacting joint remote from the longitudinal axis provides a first radial growth degree of freedom to the first gearbox relative to the longitudinal axis. A second directional reacting joint remote from the longitudinal axis provides a second radial growth degree of freedom to the first gearbox relative to the longitudinal axis. The first radial growth degree of freedom is not parallel with the second radial growth degree of freedom such that the support assembly maintains the output gear of the first gearbox in substantial collinear alignment with the input gear of the second gearbox.
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