Stators located aft of duct ring

Patent metadata

Field	Value
Publication number	US-11472533-B2
Application number	US-201916732106-A
Country	US
Kind code	B2
Filing date	Dec 31, 2019
Priority date	Dec 31, 2019
Publication date	Oct 18, 2022
Grant date	Oct 18, 2022

Abstract

A duct for a ducted-rotor aircraft includes a hub, a duct ring, and a plurality of stators that extend outward from the hub. The hub may be configured to support a motor. The duct ring defines a trailing edge. The duct ring is coupled to each of the plurality of stators such that all or substantially all of each of the plurality of stators is located aft of the trailing edge of the duct ring.

First claim

What is claimed is:

1. A duct for a ducted-rotor aircraft, the duct comprising:
a hub that is configured to support a rotor;
a duct ring that defines a trailing edge;
a plurality of stators that extend outward from the hub; and
a plurality of fittings, each of the plurality of fittings configured to couple a corresponding one of the plurality of stators to the duct ring;
wherein each of the plurality of fittings defines:
a first attachment interface that is configured to couple to structure of the duct ring; and
a second attachment interface that is configured to couple to a corresponding one of the plurality of stators;

wherein one of the plurality of fittings further defines:
a third attachment interface that is configured to at least partially receive a spindle that is rotatably couplable to a fuselage of the aircraft; and

wherein the duct ring is coupled to each of the plurality of stators such that all or substantially all of each of the plurality of stators is located aft of the trailing edge of the duct ring.

2. The duct of claim 1 , wherein the structure of the duct ring comprises first and second annular spars,
wherein the first attachment interface comprises a protrusion configured to be coupled between the first and second spars, and
wherein the second attachment interface comprises an insert configured to be received in a corresponding one of the plurality of stators.

3. The duct of claim 1 , wherein each of the plurality of fittings further defines a neck that extends from the first attachment interface to the second attachment interface.

4. The duct of claim 1 , wherein the duct ring surrounds a portion of the hub.

5. The duct of claim 1 , wherein each of the plurality of stators extends radially outward from the hub.

6. A duct for a ducted-rotor aircraft, the duct comprising:
a duct ring that defines a trailing edge; and
a first pair of stators that are coupled to the duct ring;
wherein the first pair of stators are coupled to the duct ring such that substantially all of each stator of the first pair is located aft of the trailing edge of the duct ring; and
a plurality of fittings, each of the plurality of fittings configured to couple a corresponding one of the first pair of stators to the duct ring;
wherein each of the plurality of fittings defines:
a first attachment interface that is configured to couple to structure of the duct ring; and
a second attachment interface that is configured to couple to a corresponding one of the first pair of stators; and

wherein one of the plurality of fittings further defines:
a third attachment interface that is configured to at least partially receive a spindle that is rotatably couplable to a fuselage of the aircraft.

7. The duct of claim 6 , further comprising:
a second pair of stators that are coupled to the duct ring;
wherein the second pair of stators are coupled to the duct ring such that substantially all of each stator of the second pair is located aft of the trailing edge of the duct ring.

8. The duct of claim 7 ,
wherein at least some of the plurality of fittings are each configured to couple a corresponding one of the second pair of stators to the duct ring.

9. The duct of claim 8 , wherein at least some of the plurality of fittings
each define a second attachment interface that is configured to couple to a corresponding one of the second pair of stators.

10. The duct of claim 7 , further comprising:
a hub that is configured to support a rotor, and
wherein each of the first pair of stators and each of the second pair of stators is coupled to the hub.

11. The duct of claim 10 , wherein each stator of the first pair of stators and each stator of the second pair of stators extends radially outward from the hub.

12. The duct of claim 7 , wherein the structure of the duct ring comprises first and second annular spars,
wherein the first attachment interface comprises a protrusion configured to be coupled between the first and second spars, and
wherein the second attachment interface comprises an insert configured to be received in a corresponding one of the first pair of stators or a corresponding one of the second pair of stators.

13. The duct of claim 6 , further comprising:
a hub that is configured to support a rotor,
wherein each of the first pair of stators is coupled to the hub.

14. The duct of claim 13 , wherein each stator of the first pair of stators extends radially outward from the hub.

15. The duct of claim 13 , wherein the duct ring surrounds a portion of the hub.

16. The duct of claim 6 , wherein the structure of the duct ring comprises first and second annular spars,
wherein the first attachment interface comprises a protrusion configured to be coupled between the first and second spars, and
wherein the second attachment interface comprises an insert configured to be received in a corresponding one of the first pair of stators.

17. A method of decreasing noise generated by a ducted rotor, the method comprising:
providing a duct ring that defines a trailing edge;
providing a plurality of fittings, each of the plurality of fittings defining a first attachment interface that is configured to couple to the duct ring and a second attachment interface that is configured to couple to a corresponding one of the plurality of stators, one of the plurality of fittings further defining a third attachment interface that is configured to at least partially receive a spindle; and
coupling a plurality of stators to the duct ring such that all or substantially all of each of the plurality of stators is positioned aft of the trailing edge of the duct ring;
wherein coupling the plurality of stators to the duct ring comprises:
coupling the first attachment interface of each of the plurality of fittings to the duct ring; and
coupling the second attachment interface of each of the plurality of fittings to a corresponding one of the plurality of stators.

18. The method of claim 17 , further comprising:
providing a hub that is configured to support a rotor having a plurality of blades; and
coupling the hub to each of the plurality of stators.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Feeley Elizabeth
• Schroeder Karl

Classifications

• B64C27/52

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title

• B64C11/001 Primary

  Shrouded propellers · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C27/20

  Rotorcraft characterised by having shrouded rotors, e.g. flying platforms · CPC title