Gearbox lubrication system

Patent metadata

Field	Value
Publication number	US-10190672-B2
Application number	US-201615089671-A
Country	US
Kind code	B2
Filing date	Apr 4, 2016
Priority date	Apr 4, 2016
Publication date	Jan 29, 2019
Grant date	Jan 29, 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 body;
a first rotor blade;
a drive system operable to rotate the first rotor blade, the drive system comprising:
a first gearbox assembly comprising a gearbox;
a second gearbox assembly comprising a gearbox, wherein the first gearbox assembly is in mechanical communication with the second gearbox assembly to collectively rotate the first rotor blade;
a first lubrication system configured to deliver lubricant to the first gearbox assembly;
a second lubrication system configured to deliver lubricant to the second gearbox assembly;
an emergency valve that is operable to allow the first lubrication system to deliver lubricant to the second gearbox assembly when the valve is open; and
an emergency valve control unit operable to instruct the emergency valve to open.

2. The rotorcraft of claim 1 , wherein the emergency valve control unit is operable to instruct the emergency valve to close, and the closed emergency valve inhibits the flow of lubricant from the first lubrication system to the second gearbox assembly.

3. The rotorcraft of claim 2 , wherein the first lubrication system and the second lubrication system are not in fluid communication with each other when the emergency valve is closed.

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

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

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

6. The rotorcraft of claim 1 , wherein the emergency valve control unit is operable to:
receive a rotorcraft parameter;
compare the rotorcraft parameter to a threshold value; and
if the rotorcraft parameter is less than the threshold value, instruct the emergency valve to open.

7. The rotorcraft of claim 6 , wherein the rotorcraft parameter is the pressure of the lubricant within the second lubrication system.

8. The rotorcraft of claim 1 , further comprising:
a second emergency valve that is operable to allow the second lubrication system to deliver lubricant to the first gearbox assembly when the second emergency valve is open, wherein the emergency valve control unit is further operable to instruct the second emergency valve to open.

9. The rotorcraft of claim 8 , the drive system further comprising:
a third gearbox assembly comprising a gearbox;
a third lubrication system configured to deliver lubricant to the third gearbox assembly; and
a third emergency valve that is operable to allow the first lubrication system to deliver lubricant to the third gearbox assembly, wherein the emergency valve control unit is further operable to instruct the third emergency valve to open.

10. The rotorcraft of claim 9 , further comprising:
a second drive system operable to rotate a second rotor blade, the second drive system comprising:
a first gearbox assembly comprising a gearbox;
a second gearbox assembly comprising a gearbox;
a first lubrication system configured to deliver lubricant to the first gearbox assembly;
a second lubrication system configured to deliver lubricant to the second gearbox assembly; and
an emergency valve that is operable to allow the first lubrication system to deliver lubricant to the second gearbox assembly when the valve is open;

an interconnect driveshaft in mechanical communication with the third gearbox assembly of the drive system and the first gearbox assembly of the second drive system; and
wherein the emergency valve control unit is also operable to instruct the emergency valve of the second drive system to open.

11. A method of providing emergency lubricant to a drive system of a rotorcraft, the method comprising:
providing a first lubrication system configured to deliver lubricant to a first gearbox assembly;
providing a second lubrication system configured to deliver lubricant to a second gearbox assembly, wherein the first gearbox assembly is in mechanical communication with the second gearbox assembly to collectively rotate a first rotor blade of the rotorcraft; and
opening an emergency valve to allow a flow of lubricant from the first lubrication system to the second gearbox assembly.

12. The method of claim 11 , wherein the emergency valve is a solenoid valve.

13. The method of claim 11 , wherein
the first lubrication system comprises:
a pump;
a filter; and
a lubrication line; and

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

14. The method of claim 11 , wherein the step of opening an emergency valve is in response to a rotorcraft parameter being less than a threshold value.

15. The method of claim 11 , wherein the step of opening an emergency valve is in response to the pressure of the lubricant within the second lubrication system being less than a threshold value.

16. The method of claim 11 , further comprising:
providing a third lubrication system configured to deliver lubricant to a third gearbox assembly; and
opening a second emergency valve to allow a flow of lubricant from the third lubrication system to the second lubrication system.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Ehinger Ryan T

Classifications

• B64C27/52

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

• F16H57/04

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

• F01M2001/123

  using two or more pumps · CPC title

• B64C27/006

  Safety devices · CPC title

• F16N2260/20

  Emergency · CPC title