Ducted fan assembly with a movable leading edge

Patent metadata

Field	Value
Publication number	US-2022097839-A1
Application number	US-202017036942-A
Country	US
Kind code	A1
Filing date	Sep 29, 2020
Priority date	Sep 29, 2020
Publication date	Mar 31, 2022
Grant date	—

Abstract

In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a rim that defines an opening surrounding at least a portion of the housing. The ducted fan assembly also includes a movable leading edge that is attached to the rim and extends around at least a portion of a perimeter of the ducted fan assembly, where the movable leading edge is adjustable between at least a first position and a second position.

First claim

What is claimed is:

1 . A ducted fan assembly for an aircraft comprising:
a housing comprising a rotor; a rim that defines an opening surrounding at least a portion of the housing; and a movable leading edge that is attached to the rim and extends around at least a portion of a perimeter of the ducted fan assembly, wherein the movable leading edge is adjustable between at least a first position and a second position.

2 . The ducted fan assembly of claim 1 , wherein the movable leading edge is configured to adjust to the first position during a first mode of operation of the aircraft and to adjust to the second position during a second mode of operation of the aircraft.

3 . The ducted fan assembly of claim 2 , wherein:
the aircraft is a tiltrotor aircraft; the first mode of operation comprises a helicopter mode; and the second mode of operation comprises an aircraft airplane mode.

4 . The ducted fan assembly of claim 1 , wherein the movable leading edge is mechanically actuated to adjust between the first position and the second position.

5 . The ducted fan assembly of claim 1 , wherein the movable leading edge extends outward from the rim in the first position to form a lip.

6 . The ducted fan assembly of claim 1 , wherein the movable leading edge comprises an adjustable bladder that is attached to the rim and extends around the at least a portion of a perimeter of the ducted fan assembly, the adjustable bladder comprising first and second chambers configured to be filled with a gas.

7 . The ducted fan assembly of claim 6 , wherein:
an air pressure within the first chamber remains constant in the first position and the second position; and an air pressure within the second chamber is varied between the first position and the second position.

8 . The ducted fan assembly of claim 7 , wherein the air pressure within the second chamber is increased in the second position relative to the first position.

9 . A method comprising, on an aircraft comprising a ducted fan assembly:
during a first mode of operation of the aircraft, adjusting a movable leading edge of the ducted fan assembly to a first position in which the movable leading edge extends outward from a rim of the ducted fan assembly.

10 . The method of claim 9 comprising, during a second mode of operation of the aircraft, adjusting the movable leading edge to a second position in which the movable leading edge retracts inward toward the rim.

11 . The method of claim 10 , wherein the first mode of operation comprises an airplane mode of the aircraft and the second mode of operation comprises a helicopter mode of the aircraft.

12 . A rotorcraft comprising a plurality of fan assemblies, each fan assembly comprising:
a housing comprising a rotor; a rim that defines an opening surrounding at least a portion of the housing; and a movable leading edge that is attached to the rim and extends around at least a portion of a perimeter of the fan assembly, wherein the movable leading edge is adjustable between at least a first position and a second position.

13 . The rotorcraft of claim 12 , wherein, for at least one fan assembly of the plurality of fan assemblies, the movable leading edge is configured to adjust to the first position during a first mode of operation of the aircraft and to adjust to the second position during a second mode of operation of the aircraft.

14 . The rotorcraft of claim 13 , wherein:
the rotorcraft is a tiltrotor aircraft; the first mode of operation comprises a helicopter mode; and the second mode of operation comprises an aircraft airplane mode.

15 . The rotorcraft of claim 12 , wherein, for at least one fan assembly of the plurality of fan assemblies, the movable leading edge is mechanically actuated to adjust between the first position and the second position.

16 . The rotorcraft of claim 12 , wherein, for at least one fan assembly of the plurality of fan assemblies, the movable leading edge extends outward from the rim in the first position to form a lip.

17 . The rotorcraft of claim 12 , wherein, for at least one fan assembly of the plurality of fan assemblies, the movable leading edge comprises an adjustable bladder that is attached to the rim and extends around the at least a portion of a perimeter of the ducted fan assembly, the adjustable bladder comprising first and second chambers configured to be filled with a gas.

18 . The rotorcraft of claim 17 , wherein, for at least one fan assembly of the plurality of fan assemblies:
an air pressure within the first chamber remains constant in the first position and the second position; and an air pressure within the second chamber is varied between the first position and the second position.

19 . The rotorcraft of claim 18 , wherein, for at least one fan assembly of the plurality of fan assemblies, the air pressure within the second chamber is increased in the second position relative to the first position.

20 . The rotorcraft of claim 12 , wherein one or more of the plurality of fan assemblies are ducted fan assemblies.

Assignees

• Bell Textron Inc

Inventors

• Amante William Anthony
• Carr Timothy Brian

Classifications

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• F04D29/326

  comprising a rotating shroud · CPC title

• F04D19/00 Primary

  Axial-flow pumps (F04D21/00 takes precedence; {pump comprising axial flow and radial flow stages F04D17/025}) · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F04D27/00

  Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids · CPC title