# US 12,110,826 B2 · Assembly for aircraft turbine engine comprising an improved system for lubricating a fan drive reduction gear > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,826 B2 - Document ID: US12110826B2 - Status: Granted - Kind: B2 - Application number: 17/995,204 - Filed: 2021-03-26 - Published: 2023-06-08 - Granted: 2024-10-08 - Earliest claimed: 2020-04-02 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Mohammed-Lamine Boutaleb; Nicolas Vincent Pierre-Yves Cotereau; Sébastien Oriol - Web page: https://patentgrep.com/patent/US12110826B2 ## CPC - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F01D 21/00: Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for - F01D 25/18: Lubricating arrangements (of machines or engines in general F01M) - F01D 25/20: using lubrication pumps - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/54: Radial bearings - F05D 2240/60: Shafts - F05D 2250/50: Inlet or outlet - F05D 2260/40: Transmission of power - F05D 2260/84: Redundancy - F05D 2260/98: Lubrication - F05D 2270/092: in particular blow-out and relight - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An assembly for an aircraft turbine engine includes a fan drive reduction gear and a lubrication system including: a reduction gear housing; a lubricant tank; a lubricant supply circuit including a feed pump; and a lubricant recovery circuit including a pump for recovering lubricant from the reduction gear housing. The recovery circuit includes a lubricant distributor, including: a lubricant inlet communicating with a lubricant outlet of the housing; an air inlet; and a distributor outlet, the distributor being able to adopt a lubricant recovery configuration and a configuration for retaining the lubricant in the housing. ## Claims ### Claim 1 An assembly for an aircraft turbine engine, the assembly comprising a reduction gear for driving the fan of the turbine engine, as well as a lubrication system including: a reduction gear enclosure, lubricated and containing the fan drive reduction gear; a lubricant tank; a lubricant supply circuit connecting the tank to the reduction gear enclosure, the supply circuit comprising a lubricant supply pump; a lubricant recovery circuit connecting the reduction gear enclosure to the tank, the recovery circuit comprising a pump for recovering lubricant from the reduction gear enclosure, wherein the lubricant recovery circuit includes a controlled lubricant dispenser, comprising: a lubricant inlet communicating with a lubricant outlet of the reduction gear enclosure; an air inlet; and a dispenser outlet communicating with the recovery pump, the controlled lubricant dispenser being configured to have several configurations, including: a lubricant recovery configuration, in which the controlled lubricant dispenser communicates the lubricant inlet thereof with the dispenser outlet thereof, and prohibits the communication between the air inlet thereof and the dispenser outlet thereof; and a lubricant blocking configuration in which the controlled lubricant dispenser communicates the air inlet thereof with the dispenser outlet thereof, and prohibits the communication between the lubricant inlet thereof and the dispenser outlet thereof. ### Claim 2 (depends on 1) The assembly according to claim 1, wherein the controlled lubricant dispenser is controlled depending on the lubricant pressure in the lubricant supply circuit. ### Claim 3 (depends on 2) The assembly according to claim 2, wherein the controlled lubricant dispenser includes a body, as well as a member which is movably mounted in the body between a first position bringing the controlled lubricant dispenser into the lubricant recovery configuration, and a second position bringing the controlled lubricant dispenser into the lubricant blocking configuration for blocking the lubricant in the enclosure, the movable member being subjected to a first force applied by an elastic return element forcing the movable member to the second position, and a second pressure force applied by the lubricant taken from the supply circuit, and forcing the movable member to the first position. ### Claim 4 (depends on 3) The assembly according to claim 3, wherein the controlled lubricant dispenser takes the form of an actuator whose cylinder is formed by the body and whose piston is formed by the movable member, the lubricant inlet, the air inlet, and the dispenser outlet being orifices through the cylinder. ### Claim 5 (depends on 4) The assembly according to claim 4, wherein the piston formed by the movable member includes two piston heads between which a fluid circulation chamber is defined. ### Claim 6 (depends on 1) The assembly according to claim 1, wherein the supply circuit includes a heat exchanger through which the lubricant circulates. ### Claim 7 (depends on 1) The assembly according to claim 1, further comprising: at least one turbine engine shaft rolling bearing; at least one lubricated motor enclosure containing the rolling bearing. ### Claim 8 (depends on 1) The assembly according to claim 1, further comprising: an accessory gearbox of the turbine engine; an accessory gearbox enclosure, lubricated and containing the accessory gearbox; in that the lubricant supply circuit also connects the tank to the accessory gearbox enclosure; and the lubricant recovery circuit also connects the accessory gearbox enclosure to the tank, the recovery circuit further comprising a pump for recovering lubricant from the accessory gearbox enclosure, and in that the lubricant supply pump, the pump for recovering lubricant from the accessory gearbox enclosure, as well as the pump for recovering lubricant from the reduction gear enclosure, are mechanically driven by the accessory gearbox. ### Claim 9 (depends on 1) An aircraft turbine engine comprising an assembly according to claim 1, the turbine engine including a fan driven by the reduction gear of the assembly, a compressor, and the air inlet of the controlled lubricant dispenser communicating with the compressor. ### Claim 10 (depends on 8) An aircraft turbine engine comprising the assembly according to claim 8, further comprising a fan driven by the reduction gear of the assembly, a compressor, and the air inlet of the controlled lubricant dispenser communicating with the compressor, a motor shaft mechanically driving the accessory gearbox.