# US 11,441,439 B2 · Lubricated enclosure for an aircraft turbine engine, limiting the retention of lubricant during pitching > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,441,439 B2 - Document ID: US11441439B2 - Status: Granted - Kind: B2 - Application number: 16/336,263 - Filed: 2017-09-27 - Published: 2019-07-11 - Granted: 2022-09-13 - Earliest claimed: 2016-09-29 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Serge Rene Morreale - Web page: https://patentgrep.com/patent/US11441439B2 ## CPC - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) - F01D 25/18: Lubricating arrangements (of machines or engines in general F01M) - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F16C 33/6685: {Details of collecting or draining, e.g. returning the liquid to a sump} - F16N 31/00: Means for collecting, retaining, or draining-off lubricant in or on machines or apparatus (oil separators for separating oil from exhaust steam F22G) - F05D 2220/32: in gas turbines - F05D 2260/601: using an ejector or a jet pump - F16C 2326/43: Aeroplanes; Helicopters - F16C 2360/23: Gas turbine engines - F16N 2210/02: Turbines - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - F16C: SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS - F16N: LUBRICATING - 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 A lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in the critical zone of the enclosure. The enclosure includes a device for establishing communication between the drainage orifices and the ejector, such that the lubricant that escapes from the drainage orifices supplies the ejector in order to form the primary flow. ## Claims ### Claim 1 A lubricated enclosure for an aircraft turbine engine, the enclosure comprising: a drained rolling bearing provided with drainage holes; a lubricant ejector configured to limit the retention of lubricant in a critical area of the enclosure, said ejector being configured to be traversed by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in said critical area of the enclosure; and a communication device for communicating the drainage holes with the ejector, so that the lubricant escaping from the drainage holes supplies the ejector in order to form the primary flow, wherein the secondary flow is sucked into the nozzle under effect of the primary lubricant flow flowing through the nozzle. ### Claim 2 (depends on 1) The lubricated enclosure according to claim 1, wherein the communication device is an annular lubricant manifold arranged around an outer ring of the rolling bearing, the manifold comprising a groove closed by the outer surface of the outer ring and into which the drainage holes open, said manifold also comprising at least one lubricant collection duct extending from the groove, said collection duct communicating with a primary flow inlet provided on the ejector, said duct being arranged in a 6 o'clock time position. ### Claim 3 (depends on 2) The lubricated enclosure according to claim 2, wherein the manifold is integrated with a rolling bearing support, carrying the outer ring of the bearing. ### Claim 4 (depends on 3) The lubricated enclosure according to claim 3, wherein the rolling bearing support is traversed by a lubricant discharge passage arranged opposite the nozzle of the ejector. ### Claim 5 (depends on 4) The lubricated enclosure according to claim 4, wherein the bearing support defines a radial recess in which the ejector is housed. ### Claim 6 (depends on 4) The lubricated enclosure according to claim 4, wherein the ejector comprises a generally U-shaped primary duct the primary flow inlet of which is opposite the lubricant collection duct, and an outlet of which is opposite the lubricant discharge passage. ### Claim 7 (depends on 3) The lubricated enclosure according to claim 3, wherein the bearing support also carries another bearing. ### Claim 8 (depends on 1) The lubricated enclosure according to claim 1, wherein a lubricant discharge duct extending from the ejector, said duct opening opposite a radial arm of recovering the lubricant passing through a primary flow path of the turbine engine, and arranged in a 6 o'clock time position. ### Claim 9 (depends on 1) The lubricated enclosure according to claim 1, wherein said critical area of the enclosure corresponds to a lubricant retention area formed when the turbine engine is inclined at a pitch angle, said critical area being centered in a 6 o'clock time position. ### Claim 10 (depends on 1) An aircraft turbine engine comprising at least one lubricated enclosure according to claim 1, the turbine engine comprising a fan driven by a reducer. ### Claim 11 (depends on 7) The lubricated enclosure according to claim 7, wherein the another bearing is a roller bearing.