# US 2017/0284535 A1 · Gearbox Lubrication System > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2017/0284535 A1 - Document ID: US20170284535A1 - Status: Published application - Kind: A1 - Application number: 15/089,671 - Filed: 2016-04-04 - Published: 2017-10-05 - Earliest claimed: 2016-04-04 - Assignees: Bell Helicopter Textron Inc. - Applicants: Bell Helicopter Textron Inc. - Inventors: Ryan T. Ehinger - Web page: https://patentgrep.com/patent/US20170284535A1 ## CPC - F16H 57/0442: {for supply in case of failure, i.e. auxiliary supply} - B64C 27/006: {Safety devices} - B64C 27/06: with single rotor - B64C 27/14: Direct drive between power plant and rotor hub - B64C 27/28: with forward-propulsion propellers pivotable to act as lifting rotors - B64C 27/52: Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) - B64D 35/00: Transmitting power from power plants to propellers or rotors; Arrangements of transmissions - F16H 57/04: Features relating to lubrication or cooling {or heating} (control of lubrication or cooling in hydrostatic gearing F16H61/4165) - F16H 57/0445: {for supply of different gearbox casings or sections} - B64C 29/0033: {the propellers being tiltable relative to the fuselage} - B64D 2045/0085: {Devices for aircraft health monitoring, e.g. monitoring flutter or vibration} - F01M 2001/123: {using two or more pumps} - F16N 2260/20: Emergency - F16N 2260/50: After-lubrication - F16H: GEARING - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F01M: LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING - F16N: LUBRICATING ## 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. ## Claims ### Claim 1 A rotorcraft, comprising: a body; a rotor blade; a drive system operable to rotate the rotor blade, the 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; and an emergency valve control unit operable to instruct the emergency valve to open. ### Claim 2 (depends on 1) 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 ### Claim 3 (depends on 2) 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. ### Claim 4 (depends on 1) The rotorcraft of claim 1, wherein the emergency valve is a solenoid valve. ### Claim 5 (depends on 1) 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. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 6) The rotorcraft of claim 6, wherein the rotorcraft parameter is the pressure of the lubricant within the second lubrication system. ### Claim 8 (depends on 1) 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. ### Claim 9 (depends on 8) 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; 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. ### Claim 10 (depends on 9) 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; 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; wherein the emergency valve control unit is also operable to instruct the emergency valve of the second drive system to open. ### Claim 11 A 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; 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. ### Claim 12 (depends on 11) The drive system 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. ### Claim 13 (depends on 11) The drive system of claim 11, wherein the emergency valve control unit is operable to: receive a parameter; compare the parameter to a threshold value; and if the parameter is less than the threshold value, instruct the emergency valve to open. ### Claim 14 (depends on 11) The drive system of claim 11, wherein the rotorcraft parameter is the pressure of the lubricant within the second lubrication system. ### Claim 15 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; opening an emergency valve to allow a flow of lubricant from the first lubrication system to the second gearbox assembly. ### Claim 16 (depends on 15) The method of claim 15, wherein the emergency valve is a solenoid valve. ### Claim 17 (depends on 15) The method of claim 15, 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. ### Claim 18 (depends on 15) The method of claim 15, wherein the step of opening an emergency valve is in response to a rotorcraft parameter being less than a threshold value. ### Claim 19 (depends on 15) The method of claim 15, 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. ### Claim 20 (depends on 15) The method of claim 15, further comprising: providing a third lubrication system configured to deliver lubricant to a third gearbox assembly; opening a second emergency valve to allow a flow of lubricant from the third lubrication system to the second lubrication system.