公开(公告)号：US11845534B2

公开(公告)日：2023-12-19

申请号：US16732083

申请日：2019-12-31

Applicant: Bell Textron Inc.

Inventor： Karl Schroeder ,  Jonathan Knoll ,  George Matthew Thompson

IPC: B64C11/02 ,  B64C11/00 ,  B64C29/00

CPC classification number: B64C11/02 ,  B64C11/001 ,  B64C29/0033

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.

公开(公告)号：US11772804B2

公开(公告)日：2023-10-03

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

IPC: B64D27/24 ,  B64D35/08 ,  B64C29/00

CPC classification number: B64D27/24 ,  B64C29/0033 ,  B64D35/08

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.

公开(公告)号：US11702196B2

公开(公告)日：2023-07-18

申请号：US16912513

申请日：2020-06-25

Applicant: Bell Textron Inc.

Inventor： Brad Joseph Passe ,  Nicholas Ralph Carlson ,  George Matthew Thompson

IPC: B64C27/08 ,  B64C27/37 ,  B64C27/473 ,  B64C39/02 ,  B64C29/00 ,  B64U30/20 ,  B64U50/14 ,  B64C27/54

CPC classification number: B64C27/08 ,  B64C27/37 ,  B64C27/473 ,  B64C27/54 ,  B64C29/0016 ,  B64C39/024 ,  B64U30/20 ,  B64U50/14

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.

公开(公告)号：US11459088B2

公开(公告)日：2022-10-04

申请号：US16590322

申请日：2019-10-01

Applicant: Bell Textron Inc.

Inventor： George Matthew Thompson ,  Charles Hubert Speller ,  Jonathan Knoll

IPC: B64C11/46 ,  B64C11/10 ,  B64C11/00 ,  B64C29/00 ,  B64D27/24

Abstract: A rotor assembly configured to increase the stiffness of a rotor mast. The rotor assembly includes the rotor mast, a rotor hub, a mast nut, a mast bearing, and a cuff disposed between the mast nut and the mast bearing. The cuff is captured and compressed between the mast nut and the inner race of the mast bearing along an uninterrupted load path that extends between the mast nut and the mast bearing.

公开(公告)号：US11440651B1

公开(公告)日：2022-09-13

申请号：US17188785

申请日：2021-03-01

Applicant: Bell Textron Inc.

Inventor： Andrew Paul Haldeman ,  Paul Wayne Woolbright ,  Timothy McClellan Mosig ,  George Matthew Thompson

IPC: B64C27/35 ,  B64C27/48 ,  B64C27/82

Abstract: A spherical bearing centrifugal force retention link includes an inboard spherical bearing to attach to a rotor hub and an outboard spherical bearing to attach to a rotor blade. In use, the inboard spherical bearing and the outboard spherical bearing react centrifugal force radially and a torsional moment of the centrifugal force link is substantially constant throughout the rotor blade pitch range.