# US 12,000,344 B2 · Aircraft turbine engine with an off-axis propeller > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,000,344 B2 - Document ID: US12000344B2 - Status: Granted - Kind: B2 - Application number: 17/932,934 - Filed: 2022-09-16 - Published: 2023-05-04 - Granted: 2024-06-04 - Earliest claimed: 2021-09-17 - Assignees: Safran Aircraft Engines; Safran Transmission Systems - Applicants: Safran Aircraft Engines; Safran Transmission Systems - Inventors: Paul Ghislain Albert Levisse; Julien Fabien Patrick Becoulet; Guillaume Pierre Mouly; Patrice Jocelyn Francis Gedin; Olivier Belmonte - Web page: https://patentgrep.com/patent/US12000344B2 ## 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) - B64D 35/00: Transmitting power from power plants to propellers or rotors; Arrangements of transmissions - F02C 6/206: {the vehicles being airscrew driven} - F02K 3/06: with front fan - F16H 1/28: with gears having orbital motion - F16H 1/36: with two central gears coupled by intermeshing orbital gears - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2260/40311: of the epicyclical, planetary or differential type - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - 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 ## Abstract An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear. ## Claims ### Claim 1 An aircraft turbine engine, comprising: a turbine shaft having a first axis of rotation, a propulsion propeller connected to a propeller shaft having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and configured to drive in rotation the propeller shaft, the reduction gear comprising a sun gear, a ring gear, and at least two planet gears meshed with the sun gear and the ring gear, wherein the turbine shaft is connected to the sun gear, wherein the propeller shaft is secured to the ring gear which comprises an internal toothing, wherein each of the planet gears comprises a first external toothing which is located outside the ring gear and which is meshed with an external toothing of the sun gear, wherein each of the planet gears comprises a second external toothing which is located inside the ring gear and which is meshed with the internal toothing of the ring gear, wherein the sun gear and the planet gears are located below a horizontal plane passing through the second axis, and wherein the turbine engine further comprises an equipment comprising a shaft carrying a pinion, wherein the pinion is meshed with the toothing of the ring gear and located above the horizontal plane. ### Claim 2 (depends on 1) The turbine engine according to claim 1, wherein the first toothing of each planet gear is directly meshed with the external toothing of the sun gear. ### Claim 3 (depends on 1) The turbine engine according to claim 1, wherein the first toothing of each planet gear is meshed via at least one pinion with the toothing of the sun gear. ### Claim 4 (depends on 3) The turbine engine according to claim 3, wherein the planet gears are evenly distributed about the second axis. ### Claim 5 (depends on 3) The turbine engine according to claim 3, wherein the toothing of the sun gear is meshed with the planet gears via a single pinion that is aligned with the second axis. ### Claim 6 (depends on 3) The turbine engine according to claim 3, wherein the toothing of the sun gear is meshed with the planet gears via identical K pinions, wherein K is the number of planet gears and each of the pinions is mounted between the sun gear and one of the planet gears. ### Claim 7 (depends on 6) The turbine engine according to claim 6, wherein the pinions are non-regularly distributed about the second axis. ### Claim 8 (depends on 3) The turbine engine according to claim 3, wherein the toothing of the sun gear are meshed with the planet gears by means of K pinions, at least two of which are different, wherein K is the number of planet gears and each of the pinions is mounted between the sun gear and one of the planet gears. ### Claim 9 (depends on 8) The turbine engine according to claim 8, wherein the pinions are evenly distributed about the second axis. ### Claim 10 (depends on 1) The turbine engine according to claim 1, wherein the toothing of the sun gear and the first toothing of each planet gear are each double-stage and each comprises two annular rows of teeth located at an axial distance from each other.