Ducted fan assembly with blade in leading edge

Patent metadata

Field	Value
Publication number	US-11479338-B2
Application number	US-202017037082-A
Country	US
Kind code	B2
Filing date	Sep 29, 2020
Priority date	Sep 29, 2020
Publication date	Oct 25, 2022
Grant date	Oct 25, 2022

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 extends around at least a portion of a perimeter of the ducted fan assembly, where the rim defines an opening surrounding at least a portion of the housing. The ducted fan assembly also includes a skin that is attached to the rim and extends around the at least a portion of a perimeter of the ducted fan assembly to form a leading edge of the ducted fan assembly. The ducted fan assembly also includes a blade positioned on the rim underneath the skin.

First claim

What is claimed is:

1. A ducted fan assembly comprising:
a housing comprising a rotor;
a rim that extends around at least a portion of a perimeter of the ducted fan assembly;
wherein the rim defines an opening surrounding at least a portion of the housing;
a rigid frangible skin attached to the rim and extending around the at least a portion of a perimeter of the ducted fan assembly to form a leading edge of the ducted fan assembly
a blade positioned on the rim underneath the rigid frangible skin; and
wherein the blade is in contact with less than all of a cross-sectional area of the rigid frangible skin.

2. The ducted fan assembly of claim 1 , wherein the blade structurally supports the rigid frangible skin.

3. The ducted fan assembly of claim 1 , wherein the blade has greater rigidity than the rigid frangible skin.

4. The ducted fan assembly of claim 3 , wherein the rigid frangible skin is configured to at least one of deform and break upon impact with a foreign object.

5. The ducted fan assembly of claim 4 , wherein the blade is configured to split the foreign object into two or more pieces.

6. The ducted fan assembly of claim 1 , wherein the blade comprises a peak that comes to a point.

7. The ducted fan assembly of claim 6 , wherein the peak comprises a first edge and a second edge that define a span therebetween.

8. The ducted fan assembly of claim 7 , wherein the span makes contact with the rigid frangible skin and provides structural support for the rigid frangible skin.

9. The ducted fan assembly of claim 6 , wherein the peak is offset radially inward toward a central axis of the ducted fan assembly.

10. The ducted fan assembly of claim 1 , comprising a fan positioned over the housing and attached to the rotor, wherein the fan is adjacent to the rim such that the opening defined by the rim surrounds the fan.

11. A rotorcraft comprising a plurality of fan assemblies, each fan assembly comprising:
a housing comprising a rotor;
a rim that extends around at least a portion of a perimeter of the fan assembly; wherein the rim defines an opening surrounding at least a portion of the housing;
a rigid frangible skin attached to the rim and extending around the at least a portion of a perimeter of the fan assembly to form a leading edge of the fan assembly;
a blade positioned on the rim underneath the rigid frangible skin;
wherein the blade is in contact with less than all of a cross-sectional area of the rigid frangible skin.

12. The rotorcraft of claim 11 , wherein one or more of the plurality of fan assemblies are ducted fan assemblies.

13. The rotorcraft of claim 11 , wherein the rotorcraft is a tiltrotor aircraft and the plurality of fan assemblies rotate between an airplane mode and a helicopter mode.

14. The rotorcraft of claim 11 , wherein, for each fan assembly of the plurality of fan assemblies, the blade structurally supports the rigid frangible skin and has greater rigidity than the rigid frangible skin.

15. The rotorcraft of claim 11 , wherein, for each fan assembly of the plurality of fan assemblies, the rigid frangible skin is configured to at least one of deform and break upon impact with a foreign object.

16. The rotorcraft of claim 15 , wherein, for each fan assembly of the plurality of fan assemblies, the blade is configured to split the foreign object into two or more pieces.

17. The rotorcraft of claim 11 , wherein, for each fan assembly of the plurality of fan assemblies, the blade comprises a peak that comes to a point.

18. The rotorcraft of claim 17 , wherein, for each fan assembly of the plurality of fan assemblies, the peak comprises a first edge and a second edge that define a span therebetween.

19. The rotorcraft of claim 18 , wherein, for each fan assembly of the plurality of fan assemblies, the span makes contact with the rigid frangible skin and provides structural support for the rigid frangible skin.

20. The rotorcraft of claim 18 , wherein, for each fan assembly of the plurality of fan assemblies, the peak is offset radially inward toward a central axis of the fan assembly.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Carr Timothy Brian
• Amante William Anthony
• Smith Michael Reaugh

Classifications

• B64C11/001 Primary

  Shrouded propellers · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title