Fan nozzle drive systems that lock thrust reversers

Patent metadata

Field	Value
Publication number	US-9863367-B2
Application number	US-201314070393-A
Country	US
Kind code	B2
Filing date	Nov 1, 2013
Priority date	Nov 1, 2013
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

Systems and methods are provided that lock thrust reversers and also drive fan nozzles of an aircraft. One system includes a coupling configured to selectively engage and disengage. While engaged, the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), at least a portion of which is on a translating portion of a thrust reverser of an aircraft. Furthermore, while engaged the coupling is configured to prevent displacement of the translating portion.

First claim

The invention claimed is:

1. A system comprising:
a fan nozzle drive system that locks a thrust reverser of an aircraft, the drive system comprising:
a first coupling member attached to a first structure proximate to the thrust reverser; and
a second coupling member attached to a translating portion of the thrust reverser, the translating portion configured to move relative to the first structure;
wherein the first coupling member and the second coupling member are configured to engage via motion in a direction perpendicular to a direction of translation of the translating portion;
wherein engagement of the first coupling member and the second coupling member is performed while the first coupling member and the second coupling member are aligned axially with each other, and locks the translating portion in place, preventing deployment of and movement of the translating portion in the direction of translation; and
while movement of the translating portion is prevented by the first and second coupling member, the second coupling member is configured to transmit rotation from the first coupling member to an actuator configured to drive at least a portion of a Variable Area Fan Nozzle (VAFN) located on the translating portion, thereby altering an area of an exit nozzle defined by the VAFN.

2. The system of claim 1 , wherein:
the first coupling member and the second coupling member each comprise a gear, and the gears are configured to interlock with each other in a cooperating fit.

3. The system of claim 2 , wherein:
the gears include rounded tooth edges.

4. The system of claim 2 , wherein:
teeth of the gears are configured to protrude into each other to form a Hirth coupling.

5. The system of claim 1 , wherein:
the first coupling member and the second coupling member each include a shaft, wherein the shafts are configured to rotate about a shared axis while the first and second coupling members are engaged.

6. The system of claim 1 , wherein:
the first coupling member is attached to a hinge beam of the aircraft.

7. The system of claim 1 , wherein:
the first coupling member is attached to a latch beam of the aircraft.

8. The system of claim 1 , wherein:
the first coupling member is attached to a turbofan engine of the aircraft.

9. The system of claim 1 , wherein:
the VAFN is a petal-type VAFN.

10. The system of claim 1 , wherein:
the first coupling member includes a retractable portion configured for cooperating fit with the second coupling member, and
the first coupling member is configured to disengage from the second coupling member by retracting the retractable portion.

11. The system of claim 1 , wherein:
the first coupling member and the second coupling member are configured to engage with each other to form a frictional cooperating fit.

12. The system of claim 1 , further comprising:
a bevel gear coupled to the second coupling member, the bevel gear configured to drive a rotary actuator for the VAFN.

13. A system comprising:
a fan nozzle drive system that locks a thrust reverser of an aircraft, the drive system comprising:
a coupling configured to selectively engage and disengage first and second coupling members, via motion in a direction perpendicular to a direction of translation of a translating portion of a thrust reverser of an aircraft, wherein:
while engaged, the first and second coupling members are axially aligned with each other, and the coupling is configured to rotate to drive a Variable Area Fan Nozzle (VAFN), thereby altering an area of an exit nozzle defined by the VAFN, wherein
at least a portion of the coupling is on a translating portion of the thrust reverser and
while engaged, the coupling locks the translating portion in place, preventing movement of the translating portion.

14. The system of claim 13 , wherein:
the first coupling member and the second coupling member are configured for cooperating fit with each other, wherein the second coupling member is attached to the translating portion of the thrust reverser, and the first coupling member is attached to a portion of the aircraft that is fixed with respect to the translating portion.

15. The system of claim 14 , wherein:
the first coupling member is attached to a hinge beam or a latch beam of the aircraft.

16. The system of claim 14 , wherein:
the first coupling member is arranged perpendicular to a direction of motion of the translating portion, the first coupling member configured to inhibit movement of the translating portion when the first coupling member is engaged with the second coupling member, by resisting shear forces applied to the first coupling member when the translating portion attempts to move.

17. The system of claim 14 , wherein:
the first coupling member is configured to disengage from the second coupling member by retracting.

18. The system of claim 14 , wherein:
the first coupling member and the second coupling member are configured to protrude into each other to form a Hirth coupling.

19. A method of operating a Variable Area Fan Nozzle (VAFN) located on a transcowl of an aircraft, the method comprising:
closing a transcowl of a thrust reverser of an aircraft;
engaging a coupling of a fan nozzle drive system by engaging first and second coupling members via motion in a direction perpendicular to a direction of translation of the transcowl, thereby locking the transcowl in place in a closed position, wherein the transcowl includes a movable petal of a VAFN;
while engaged, the coupling locks the translating portion in place, preventing deployment of and movement of the translating portion in the direction of translation, and
rotating the coupling to move the movable petal while the coupling is engaged, thereby altering an area of an exit nozzle defined by the VAFN.

20. The method of claim 19 , further comprising:
disengaging the coupling to enable movement of the transcowl.

21. An apparatus comprising:
a fan nozzle drive system that locks a thrust reverser of an aircraft, the drive system comprising:
a motor; and
a coupling that comprises:
a first interlock gear coupled to the motor; and
a second interlock gear coupled to a Variable Area Fan Nozzle (VAFN),

wherein:
in a first mode of operation, the first and second interlock gears are axially aligned and engaged with each other to enable the motor to apply torque to the coupling in a manner that drives the VAFN, while the coupling locks a translating portion of the thrust reverser in place, preventing deployment and movement of the translating portion in a direction of translation of the translating portion, and
in a second mode of operation the first and second interlock gears are disengaged to allow the thrust reverser to move,
wherein the first coupling member and the second coupling member are configured to engage via motion in a direction perpendicular to the direction of translation of the translating portion.

22. The apparatus of claim 21 wherein:
in the first mode of operation the motor is configured to drive the VAFN by applying torque that displaces a track within the VAFN.

23. The apparatus of claim 22 wherein:
the track includes multiple rollers that each correspond to a petal of the VAFN, and torque applied by the motor causes each of the rollers to change position by moving along a ramp, resulting in a change of position of a corresponding petal of the VAFN.

Assignees

• Boeing Co

Inventors

• Burghdoff Michael J
• Farstad Jerry Edward

Classifications

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2270/051

  Thrust · CPC title

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F02K1/625

  the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title

• F02K1/766 Primary

  with blocking systems or locking devices; Arrangement of locking devices for thrust reversers · CPC title