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公开(公告)号：US20210403149A1
公开(公告)日：2021-12-30
申请号：US16912513
申请日：2020-06-25
Applicant: Bell Textron Inc.
Inventor： Brad Joseph Passe , Nicholas Ralph Carlson , George Matthew Thompson
Abstract: A rotor system includes a rotor assembly and a duct system. The rotor assembly includes rotor blades extending from a mast axis and configured to rotate about the mast axis. The duct assembly includes a moveable duct portion and a stationary duct portion. In a first duct configuration, the moveable duct portion surrounds a first portion of the rotor assembly, the stationary duct portion surrounds a second portion of the rotor assembly, and the moveable duct portion and the stationary duct portion enclose the rotor assembly. In a second duct configuration, the stationary duct portion surrounds the second portion of the rotor assembly, and the moveable duct portion is moved away from the first portion of the rotor assembly, such that the rotor assembly is not enclosed.
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公开(公告)号：US20210387722A1
公开(公告)日：2021-12-16
申请号：US16900543
申请日：2020-06-12
Applicant: Bell Textron Inc.
Inventor： Timothy Brian Carr , George Matthew Thompson
Abstract: One embodiment is a rotor system comprising a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises an outboard end; a tip extension mechanism affixed at the outboard end of the at least one rotor blade, wherein the tip extension mechanism comprises at least one shim, the at least one rotor blade with the tip extension mechanism affixed thereto comprising an extended rotor blade; and a blade tip affixed to an outboard end of the extended rotor blade, wherein the blade tip is affixed to the extended rotor blade via at least one removable fastener.
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公开(公告)号：US20210197956A1
公开(公告)日：2021-07-01
申请号：US16732083
申请日：2019-12-31
Applicant: Bell Textron Inc.
Inventor： Karl Schroeder , Jonathan Knoll , George Matthew Thompson
Abstract: A ducted-rotor aircraft includes a fuselage and first and second ducts that are coupled to the fuselage. Each duct includes a duct ring, a rotor having a plurality of blades, a hub that positions the rotor such that the blades define a blade plane of rotation within the duct ring, and a plurality of stators that are coupled to the hub at respective locations aft of the blade plane of rotation. Each of the plurality of stators defines a leading edge that is slanted toward the blade plane of rotation. The leading edges of the stators are slanted to follow a contour defined by the blades. The leading edges may also be slanted to maintain a distance of at least one blade inboard chord length between the leading edges of the stators and respective trailing edges of the blades.
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公开(公告)号：US20210139157A1
公开(公告)日：2021-05-13
申请号：US16679000
申请日：2019-11-08
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Paul Sherrill , Jonathan Knoll
Abstract: A rotor assembly including a rotor mast, a rotor hub coupled to the rotor mast, a plurality of rotor blades coupled to the rotor hub, a control tube extending through the rotor mast, a crosshead coupled to the control tube, and a mechanism configured to drive the rotor mast in rotation. Wherein the mechanism is longitudinally positioned between a top portion and a bottom portion of the control tube and translation of the control tube relative to the rotor mast causes rotation of the rotor blades about their pitch-change axes. While the crosshead is installed, the crosshead is prevented from angular rotation about the mast axis. A pin of a rotor blade assembly is captured between opposing tabs of the crosshead and movable relative to the opposing tabs in response to translation of the crosshead along the mast axis
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公开(公告)号：US20210094673A1
公开(公告)日：2021-04-01
申请号：US16590223
申请日：2019-10-01
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Jonathan Knoll , Paul Sherrill
Abstract: A rotor assembly has a rotor hub having a unitary structure. The rotor assembly further includes a unitary crosshead having a first upper tab and a first lower tab located vertically below the first upper tab. The first upper tab and the first lower tab define a slot therebetween to accept a first pin of the first rotor blade. A second upper tab and a second lower tab located vertically below the second upper tab define a slot therebetween to accept a second pin of the second rotor blade. A first recess is provided between the first lower tab and the second lower tab so that the crosshead comprises no material directly between at least a portion of the first lower tab and the second lower tab along at least one straight path.
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Patent Agency Ranking
公开(公告)号：US11453491B2
公开(公告)日：2022-09-27
申请号：US17173860
申请日：2021-02-11
Applicant: Bell Textron Inc.
Inventor： Elizabeth Feeley , Karl H. Schroeder , George Matthew Thompson , Michael Mark Attaway , Joseph Richard Carpenter, Jr.
Abstract: One embodiment is a rotor system comprising a duct ring; a hub disposed centrally to the duct ring; first and second stators each connected between the duct ring and the hub; first and second control vanes rotatably connected to the first and second stators, respectively; a structural hoop having a first end connected to the first control vane and a second end connected to the second control vane, the structural hoop for translating rotation of the first control vane about a vane axis to the second control vane; and a mechanism for restricting at least one of forward-aft movement and side-to-side movement of the structural hoop relative to the duct ring.
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公开(公告)号：US11420762B2
公开(公告)日：2022-08-23
申请号：US16679000
申请日：2019-11-08
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Paul Sherrill , Jonathan Knoll
Abstract: A rotor assembly including a rotor mast, a rotor hub coupled to the rotor mast, a plurality of rotor blades coupled to the rotor hub, a control tube extending through the rotor mast, a crosshead coupled to the control tube, and a mechanism configured to drive the rotor mast in rotation. Wherein the mechanism is longitudinally positioned between a top portion and a bottom portion of the control tube and translation of the control tube relative to the rotor mast causes rotation of the rotor blades about their pitch-change axes. While the crosshead is installed, the crosshead is prevented from angular rotation about the mast axis. A pin of a rotor blade assembly is captured between opposing tabs of the crosshead and movable relative to the opposing tabs in response to translation of the crosshead along the mast axis.
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公开(公告)号：US20220219826A1
公开(公告)日：2022-07-14
申请号：US17148273
申请日：2021-01-13
Applicant: Bell Textron Inc.
Inventor： Jonathan Andrew Knoll , George Matthew Thompson , Charles Hubert Speller , Grant Michael Beall
Abstract: A rotor system for an aircraft is described and includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for providing rotational energy to a motor shaft; and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the motor shaft and providing rotational energy to the rotor mast via a rotor shaft.
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公开(公告)号：US20210316849A1
公开(公告)日：2021-10-14
申请号：US16846371
申请日：2020-04-12
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Jonathan Andrew Knoll , Nicholas Carlson
Abstract: A rotor blade retention device for use in an aircraft having a plurality of blades includes an array of cavities, each cavity adapted to receive a portion of a tension-torsion strap therein. Each cavity is oriented such that, when the portion of the tension-torsion strap is received therein, a central plane of the tension-torsion strap is inclined relative to a blade plane of rotation defined by the plurality of blades. The retention device may have a body that defines an aperture adapted to receive a portion of a rotor mast of the aircraft, may comprise a rotor mast of the aircraft, or may comprise first and second plates that cooperate to form the array of cavities and that are adapted to receive a portion of the rotor mast of the aircraft.
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公开(公告)号：US11104414B2
公开(公告)日：2021-08-31
申请号：US16590223
申请日：2019-10-01
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Jonathan Knoll , Paul Sherrill
Abstract: A rotor assembly has a rotor hub having a unitary structure. The rotor assembly further includes a unitary crosshead having a first upper tab and a first lower tab located vertically below the first upper tab. The first upper tab and the first lower tab define a slot therebetween to accept a first pin of the first rotor blade. A second upper tab and a second lower tab located vertically below the second upper tab define a slot therebetween to accept a second pin of the second rotor blade. A first recess is provided between the first lower tab and the second lower tab so that the crosshead comprises no material directly between at least a portion of the first lower tab and the second lower tab along at least one straight path.
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