# US 11,306,813 B2 · Passive planetary emergency lubrication system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,306,813 B2 - Document ID: US11306813B2 - Status: Granted - Kind: B2 - Application number: 16/657,166 - Filed: 2019-10-18 - Published: 2021-04-22 - Granted: 2022-04-19 - Earliest claimed: 2019-10-18 - Assignees: Textron Innovations Inc. - Applicants: Bell Textron Inc. - Inventors: Douglas Robert Mueller - Web page: https://patentgrep.com/patent/US11306813B2 ## CPC - F16H 57/0442: {for supply in case of failure, i.e. auxiliary supply} - B64C 29/0033: {the propellers being tiltable relative to the fuselage} - B64D 35/00: Transmitting power from power plants to propellers or rotors; Arrangements of transmissions - F16H 57/0441: {Arrangements of pumps} - F16H 57/0443: {for supply of lubricant during tilt or high acceleration, e.g. problems related to the tilt or extreme acceleration of the transmission casing and the supply of lubricant under these conditions} - F16H 57/0445: {for supply of different gearbox casings or sections} - F16H 57/045: {Lubricant storage reservoirs, e.g. reservoirs in addition to a gear sump for collecting lubricant in the upper part of a gear case} - F16H 57/0456: {Lubrication by injection; Injection nozzles or tubes therefor (oil mist or spray lubrication F16H57/0458)} - F16H 57/0482: {Gearings with gears having orbital motion} - F16H 57/0486: {with fixed gear ratio (axle or inter-axle differentials F16H57/0483)} - F16N 29/02: for influencing the supply of lubricant - F16N 2210/08: Aircraft - F16N 2270/70: Supply - F16N 2280/00: Valves - 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 - F16N: LUBRICATING ## Abstract An example of an emergency lubrication system for an aircraft includes a lubricant tank configured to supply a lubricant to a gearbox of the aircraft, a tube coupled between the lubricant tank and the gearbox and comprising a check ball disposed within the tube, a first lubricant line coupled to the tube and a first inlet of the gearbox, and a second lubricant line coupled to the tube and a second inlet of the gearbox. ## Claims ### Claim 1 An emergency lubrication system for an aircraft, the emergency lubrication system comprising: a lubricant tank configured to supply a lubricant to a gearbox of the aircraft; a tube coupled between the lubricant tank and the gearbox and comprising a check ball disposed within the tube; a first lubricant line coupled to the tube and a first inlet of the gearbox; and a second lubricant line coupled to the tube and a second inlet of the gearbox; wherein the tube is oriented so that the check ball moves to a first end of the tube to block a flow of the lubricant to the first lubricant line when the gearbox is oriented in a first configuration and so that the check ball moves to a second end of the tube to block the flow of the lubricant to the second lubricant line when the gearbox is oriented in a second configuration. ### Claim 2 (depends on 1) The emergency lubrication system of claim 1, wherein the lubricant is provided to the gearbox at a first location when the gearbox is oriented in the first configuration and the lubricant is provided to the gearbox at a second location when the gearbox is oriented in the second configuration. ### Claim 3 (depends on 2) The emergency lubrication system of claim 2, wherein the first location is a first side of an interface of a planetary gear and a ring gear of the gearbox and wherein the second location is a second side of an interface of the planetary gear and the ring gear. ### Claim 4 (depends on 1) The emergency lubrication system of claim 1, wherein: the lubricant tank comprises an outlet; and the outlet is positioned at a height above the first and second inlets to allow a gravity feed of the lubricant from the lubricant tank to the gearbox. ### Claim 5 (depends on 1) The emergency lubrication system of claim 1, comprising a pump disposed within the lubricant tank and configured to supply the lubricant to the gearbox. ### Claim 6 (depends on 1) The emergency lubrication system of claim 1, wherein the first lubricant line comprises a first jet configured to inject the lubricant at a first location within the gearbox and the second lubricant line comprises a second jet configured to inject the lubricant at a second location within the gearbox. ### Claim 7 A lubrication system for an aircraft, the lubrication system comprising: a primary lubrication system for a gearbox of the aircraft, the primary lubrication system comprising a first lubricant tank; an emergency lubrication system for the gearbox, the emergency lubrication system comprising: a second lubricant tank configured to supply a lubricant to a gearbox of the aircraft; a tube coupled between the second lubricant tank and the gearbox and comprising a check ball disposed within the tube; a first lubricant line coupled to the tube and a first inlet of the gearbox; and a second lubricant line coupled to the tube and a second inlet of the gearbox; wherein the tube is oriented so that the check ball moves to a first end of the tube to block a flow of the lubricant to the first lubricant line when the gearbox is oriented in a first configuration and so that the check ball moves to a second end of the tube to block the flow of the lubricant to the second lubricant line when the gearbox is oriented in a second configuration. ### Claim 8 (depends on 7) The lubrication system of claim 7, wherein the lubricant is provided to the gearbox at a first location when the gearbox is oriented in the first configuration and the lubricant is provided to the gearbox at a second location when the gearbox is oriented in the second configuration. ### Claim 9 (depends on 8) The lubrication system of claim 8, wherein the first location is a first side of an interface of a planetary gear and a ring gear of the gearbox and wherein the second location is a second side of an interface of the planetary gear and the ring gear. ### Claim 10 (depends on 7) The lubrication system of claim 7, wherein: the second lubricant tank comprises an outlet; and the outlet is positioned at a height above the first and second inlets to allow a gravity feed of the lubricant from the second lubricant tank to the gearbox. ### Claim 11 (depends on 7) The lubrication system of claim 7, comprising a pump disposed within the second lubricant tank and configured to supply the lubricant to the gearbox. ### Claim 12 (depends on 7) The lubrication system of claim 7, wherein the first lubricant line comprises a first jet configured to inject the lubricant at a first location within the gearbox and the second lubricant line comprises a second jet configured to inject the lubricant at a second location within the gearbox. ### Claim 13 A method of providing emergency lubrication for an aircraft, the method comprising: determining if a loss of lubrication event has occurred; responsive to a determination that the loss of lubrication event has occurred, opening a valve of an emergency lubrication system to provide lubricant to a gearbox of the aircraft; wherein the emergency lubrication system comprises: a lubricant tank configured to supply a lubricant to a gearbox of the aircraft; a tube coupled between the lubricant tank and the gearbox and comprising a check ball disposed within the tube; a first lubricant line coupled to the tube and a first inlet of the gearbox; and a second lubricant line coupled to the tube and a second inlet of the gearbox; wherein: the check ball is positioned to block a flow of the lubricant to the first lubricant line when the gearbox is oriented in a first orientation; and the check ball is positioned to block the flow of the lubricant to the second lubricant line when the gearbox is oriented in a second orientation. ### Claim 14 (depends on 13) The method of claim 13, comprising providing the lubricant from the lubricant tank to the gearbox via the first lubricant line when the gearbox is in the first orientation; and providing the lubricant from the lubricant tank to the gearbox via the second lubricant line when the gearbox is in the second orientation. ### Claim 15 (depends on 13) The method of claim 13, wherein: the lubricant tank comprises an outlet; and the outlet is positioned at a height above the first and second inlets to allow a gravity feed of the lubricant from the lubricant tank to the gearbox. ### Claim 16 (depends on 13) The method of claim 13, wherein the emergency lubrication system comprises a pump disposed within the lubricant tank and configured to supply the lubricant to the gearbox. ### Claim 17 (depends on 13) The method of claim 13, wherein the first lubricant line comprises a first jet configured to inject the lubricant at a first location within the gearbox and the second lubricant line comprises a second jet configured to inject the lubricant at a second location within the gearbox.