Gearbox lubrication system

Patent metadata

Field	Value
Publication number	US-10443706-B2
Application number	US-201816181641-A
Country	US
Kind code	B2
Filing date	Nov 6, 2018
Priority date	Apr 4, 2016
Publication date	Oct 15, 2019
Grant date	Oct 15, 2019

Abstract

According to one embodiment, a rotorcraft includes a body, a rotor blade, a drive system that can be operated to rotate the rotor blade, and an emergency valve control unit. The drive system contains a first gearbox assembly, a second gearbox assembly, a first lubrication system that can deliver lubricant to the first gearbox assembly, and a second lubrication system that can deliver lubricant to the second gearbox assembly. The drive system also contains an emergency valve that can be opened to deliver lubricant from the first lubrication system to the second gearbox assembly. The emergency valve control unit can instruct the emergency valve to open.

First claim

What is claimed is:

1. A rotorcraft comprising:
a drive system, the drive system comprising:
a first gearbox assembly;
a second gearbox assembly, wherein the first gearbox assembly is in mechanical communication with the second gearbox assembly;
a first lubrication system associated with the first gearbox assembly;
a second lubrication system associated with the second gearbox assembly;
a valve operable to allow lubricant to be delivered from the first lubrication system to the second gearbox assembly when the valve is open; and
a control unit operable, at least in part, to instruct the valve to open or close.

2. The rotorcraft of claim 1 , wherein the first lubrication system and the second lubrication system are not in fluid communication when the valve is closed.

3. The rotorcraft of claim 1 , wherein control unit is further operable, at least in part, to:
receive a rotorcraft parameter;
compare the rotorcraft parameter to a threshold value; and
instruct the valve to open when the rotorcraft parameter is less than the threshold value.

4. The rotorcraft of claim 3 , wherein the rotorcraft parameter is at least one of a pressure or a level associated with lubricant within the second lubrication system.

5. The rotorcraft of claim 1 , wherein the valve is a solenoid valve.

6. The rotorcraft of claim 1 , wherein the drive system is operable to rotate a rotor blade.

7. The rotorcraft of claim 1 , wherein the drive system is operable to provide power to one or more accessory devices.

8. The rotorcraft of claim 1 , wherein
the first lubrication system comprises:
a pump;
a filter; and
at least one lubrication line; and

the second lubrication system comprises:
a pump;
a filter; and
at least one lubrication line.

9. The rotorcraft of claim 1 , wherein the valve is a first valve, the drive system further comprising:
a second valve operable to allow lubricant to be delivered from the second lubrication system to the first gearbox assembly when the second valve is open, wherein the control unit is further operable, at least in part, to instruct the second valve to open or close.

10. The rotorcraft of claim 9 , the drive system further comprising:
a third gearbox assembly;
a third lubrication system associated with the third gearbox assembly; and
a third valve operable to allow lubricant to be delivered from the first lubrication system to the third gearbox assembly, wherein the control unit is further operable, at least in part, to instruct the third valve to open or close.

11. The rotorcraft of claim 10 , wherein the drive system is a first drive system, the rotorcraft further comprising:
a second drive system, the second drive system further comprising:
a first gearbox assembly;
a second gearbox assembly, wherein the first gearbox assembly is in mechanical communication with the second gearbox assembly;
a first lubrication system associated with the first gearbox assembly;
a second lubrication system associated with the second gearbox assembly; and
a valve operable to allow lubricant to be delivered from the first lubrication system to the second gearbox assembly when the valve is open, wherein the control unit is further operable, at least in part, to instruct the valve to open or close.

12. The rotorcraft of claim 11 , wherein the second drive system is operable to rotate a rotor blade.

13. The rotorcraft of claim 11 , wherein the second drive system is operable to provide power to one or more accessory devices.

14. The rotorcraft of claim 11 , wherein the valve of the second drive system is a solenoid valve.

15. The rotorcraft of claim 11 , wherein
the first lubrication system of the second drive system comprises:
a pump;
a filter; and
at least one lubrication line; and

the second lubrication system of the second drive system comprises:
a pump;
a filter; and
at least one lubrication line.

16. The rotorcraft of claim 11 , further comprising:
an interconnect driveshaft, wherein the interconnect driveshaft is in mechanical communication with the third gearbox assembly and the interconnect driveshaft is in mechanical communication with the first gearbox assembly of the second drive system.

17. The rotorcraft of claim 16 , further comprising:
a first engine in mechanical communication with the first drive system; and
a second engine in mechanical communication with the second drive system.

18. The rotorcraft of claim 17 , wherein the first drive system is operable to provide power to the second drive system via the interconnect driveshaft when the second engine is inoperable.

19. The rotorcraft of claim 17 , wherein the second drive system is operable to provide power to the first drive system via the interconnect driveshaft when the first engine is inoperable.

20. The rotorcraft of claim 1 , wherein the control unit is a computing device comprising:
at least one memory element operable to store data; and
at least one processor operable to execute instructions associated with the data.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Ehinger Ryan T

Classifications

• F16H57/04

  Features relating to lubrication or cooling {or heating} (control of lubrication or cooling in hydrostatic gearing F16H61/4165) · CPC title

• B64C27/14

  Direct drive between power plant and rotor hub · CPC title

• F01M2001/123

  using two or more pumps · CPC title

• F16H57/0442 Primary

  for supply in case of failure, i.e. auxiliary supply · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title