# US 11,994,073 B2 · Aircraft turbomachine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,994,073 B2 - Document ID: US11994073B2 - Status: Granted - Kind: B2 - Application number: 17/906,790 - Filed: 2021-03-25 - Published: 2023-05-11 - Granted: 2024-05-28 - Earliest claimed: 2020-03-27 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Paul Ghislain Albert Levisse; Julien Fabien Patrick Becoulet - Web page: https://patentgrep.com/patent/US11994073B2 ## CPC - 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) - F01D 15/12: Combinations with mechanical gearing (driven by multiple engines F01D13/00) - F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) - F02C 3/06: the compressor comprising only axial stages (F02C3/10 takes precedence) - F02C 3/107: with two or more rotors connected by power transmission - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F02K 3/06: with front fan - F16H 1/28: with gears having orbital motion - F01D 25/162: {Bearing supports} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/50: Bearings - F05D 2250/36: in inner-outer relationship, e.g. shaft-bearing arrangements - F05D 2250/611: undulated - F05D 2260/40: Transmission of power - F05D 2260/40311: of the epicyclical, planetary or differential type - F05D 2260/96: Preventing, counteracting or reducing vibration or noise - 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) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F16H: GEARING - 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 Aircraft turbomachine comprising a casing, a fan, a compressor and a turbine and an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by the ring gear of the first output stage. ## Claims ### Claim 1 An aircraft turbomachine comprising a casing, a fan, a compressor and a turbine, the casing comprising an inlet casing between the fan and the compressor, the turbomachine further comprising an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by a first ring gear, the first ring gear being the ring gear of the first output stage, wherein the first ring gear is radially outside of at least one planet gear of the first output stage. ### Claim 2 (depends on 1) The turbomachine according to claim 1, wherein the fan is driven in rotation by a second ring gear, the second ring gear being the ring gear of the second output stage. ### Claim 3 (depends on 1) The turbomachine according to claim 1, wherein the at least one planet gear comprises a first wheel and a second wheel secured in rotation to each other, the first wheel belonging to the first output stage and meshing with the ring gear of the first output stage and the second wheel belonging to the second output stage. ### Claim 4 (depends on 3) The turbomachine according to claim 3, wherein a ratio between a diameter of the first output wheel and a diameter of the second output wheel is comprised between 0.5 and 10. ### Claim 5 (depends on 1) The turbomachine according to claim 1, wherein the epicyclic gear train comprises a planet carrier fixed relative to the casing. ### Claim 6 (depends on 1) The turbomachine according to claim 1, wherein the input comprises a sun gear of the epicyclic gear train. ### Claim 7 (depends on 1) The turbomachine according to claim 1, wherein the compressor is supported relative to the casing by at least one bearing. ### Claim 8 (depends on 1) The turbomachine according to claim 1, further comprising a bearing arranged between a shaft of the compressor and a shaft of the turbine. ### Claim 9 (depends on 1) The turbomachine according to claim 1, wherein three elements among a fan shaft, a compressor shaft, a turbine shaft and the casing comprise a locally more flexible portion able to accommodate axial displacements of said elements. ### Claim 10 (depends on 9) The turbomachine according to claim 9, wherein said portion has meanders in axial section. ### Claim 11 (depends on 1) The turbomachine according to claim 1, wherein said fan is the only fan of the turbomachine. ### Claim 12 (depends on 1) The turbomachine according to claim 1, wherein said compressor is a low-pressure compressor and the turbomachine further comprises a high-pressure compressor downstream of the low-pressure compressor, the casing comprising an inter-compressor casing between the low-pressure compressor and the high-pressure compressor. ### Claim 13 (depends on 1) The turbomachine according to claim 1, wherein a fan shaft is supported relative to the inlet casing by at least one bearing.