# US 12,110,829 B2 · Turbomachine fan assembly comprising a roller bearing and a double-row ball bearing with oblique contact > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,829 B2 - Document ID: US12110829B2 - Status: Granted - Kind: B2 - Application number: 17/754,167 - Filed: 2020-09-07 - Published: 2022-09-15 - Granted: 2024-10-08 - Earliest claimed: 2019-09-27 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: François Marie Paul Marlin; Didier Gabriel Bertrand Desombre; Christophe Paul Jacquemard; Laurent Paul François Perrot - Web page: https://patentgrep.com/patent/US12110829B2 ## 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 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F16C 19/181: {with angular contact} - F16C 19/505: {with the diameter of the rolling elements of one row differing from the diameter of those of another row} - F16C 19/54: Systems consisting of a plurality of bearings with rolling friction (spindle bearings F16C35/08) - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2240/50: Bearings - F05D 2240/54: Radial bearings - F05D 2250/73: asymmetric - F16C 2360/23: Gas turbine engines - 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) - F16C: SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS - 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 aircraft propulsion assembly including a fan shaft which is connected to a turbine shaft by means of a reduction gear. The guiding of the fan shaft is carried out by a first bearing including cylindrical rollers and a second beating including two rows of balls with oblique contact. ## Claims ### Claim 1 A fan assembly for an aircraft turbomachine, the assembly comprising a fan shaft and first and second bearings configured to guide the fan shaft in rotation about a central axis, wherein the first bearing has cylindrical rollers and the second bearing has a double-row of balls with oblique contact, wherein the second bearing comprises first and second rows of balls, and an inner ring and an outer ring each comprising first and second races, the first race of the inner and outer rings receiving the first row of balls, the second race of the inner and outer rings receiving the second row of balls, and wherein the fan shaft comprises a first support portion carrying an inner ring of the first bearing, a second support portion carrying an inner ring of the second bearing, a first frustoconical junction portion connecting together the first and second support portions, and a second frustoconical junction portion intended to connect together the second support portion and a reduction gear of the turbomachine, said second support portion having a thickness taken perpendicular to a longitudinal extent thereof that is larger than a thickness of the first frustoconical junction portion taken perpendicular to a longitudinal extent thereof and a thickness of the second frustoconical junction portion taken perpendicular to a longitudinal extent thereof. ### Claim 2 (depends on 1) The assembly according to claim 1, wherein one amongst the inner and outer rings of the second bearing comprises a first half-ring forming the first race of this ring and a second half-ring forming the second race of this ring. ### Claim 3 (depends on 1) The assembly according to claim 1, wherein the balls of the first row have a diameter different from the balls of the second row, such that the ratio of the diameter of the balls of one of these rows and the diameter of the balls of the other row is higher than 1.5. ### Claim 4 (depends on 1) The assembly according to claim 1, wherein the first and second races of the outer ring of the second bearing are axially located between the first and second races of the inner ring of the second bearing. ### Claim 5 (depends on 1) The assembly according to claim 1, further comprising a fixed support configured to support an outer ring of the second bearing, the support and the outer ring of the second bearing each comprising a connecting element forming a respective bearing surface, said connecting elements being configured so that: a force applied on the fan shaft according to a first direction along said central axis tends to press against each other the bearing surfaces of said connecting elements, a force applied on the fan shaft according to a second direction along said central axis tends to bring the bearing surfaces of said connecting elements away from each other. ### Claim 6 (depends on 1) An aircraft turbomachine, said turbomachine comprising a fan assembly according to claim 1. ### Claim 7 (depends on 6) The turbomachine according to claim 6, further comprising a turbine shaft and a reduction gear configured to reduce the rotational speed between the turbine shaft and the fan shaft. ### Claim 8 (depends on 6) A propulsion unit for an aircraft, said propulsion unit comprising a turbomachine according to claim 6.