# US 10,502,144 B2 · Gas turbine engine with a geared turbofan arrangement > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,144 B2 - Document ID: US10502144B2 - Status: Granted - Kind: B2 - Application number: 15/708,716 - Filed: 2017-09-19 - Published: 2018-03-22 - Granted: 2019-12-10 - Earliest claimed: 2016-09-20 - Assignees: Rolls-Royce Deutschland Ltd & Co KG - Applicants: Rolls-Royce Deutschland Ltd & Co KG - Inventors: Dominic Boniface - Web page: https://patentgrep.com/patent/US10502144B2 ## 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) - F02K 3/06: with front fan - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2240/20: Rotors - F05D 2240/54: Radial bearings - F05D 2240/60: Shafts - 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) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine engine, in particular an aircraft engine is provided. The gas turbine engine including a geared turbofan arrangement, a propulsive fan and a planetary gearbox being driveably connected with a first shaft on the output side of the planetary gearbox and a second shaft on the input side of the planetary gearbox. The propulsive fan is supported through a front load path and a rear load path, the front load path including a first bearing between the first shaft and a sun gear, the rear load path including a second bearing between the second shaft and a fixed structure of the gas turbine engine. The first shaft including a first portion of the shaft as torque carrying part, wherein the torque carrying part including a torque carrying coupling being connected to the first shaft and to a carrier of the planetary gearbox. ## Claims ### Claim 1 A gas turbine engine, comprising: a propulsive fan, a first shaft, a second shaft, a planetary gearbox including a sun gear, a carrier, an output side and an input side, the planetary gearbox being driveably connected with the first shaft on the output side and with the second shaft on the input side, wherein the propulsive fan is supported through a front load path and a rear load path, wherein: the front load path comprises a first bearing as an intershaft bearing between the first shaft and the sun gear, the rear load path comprises a second bearing between the second shaft and a fixed structure of the gas turbine engine, the second shaft being supported by the second bearing and the fixed structure, and the first shaft comprises a first portion of the shaft as a torque carrying part, the torque carrying part comprises a torque carrying coupling being connected to the first shaft and to the carrier, the propulsive fan is connected to the first shaft and driven by the carrier. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the first bearing is a radial rolling bearing. ### Claim 3 (depends on 1) The gas turbine engine according to claim 1, wherein the first bearing is a tapered roller bearing. ### Claim 4 (depends on 1) The gas turbine engine according to claim 1, wherein the second bearing is a radial rolling bearing. ### Claim 5 (depends on 1) The gas turbine engine according to claim 1, wherein the second shaft is connected to or integral with the sun gear of the planetary gearbox. ### Claim 6 (depends on 1) The gas turbine engine according to claim 1, and further comprising a spline connection between the sun gear and the second shaft, wherein the sun gear is driven through the spline connection by the second shaft. ### Claim 7 (depends on 1) The gas turbine engine according to claim 1, and further comprising a third bearing located between the first portion of the first shaft and a second portion of the first shaft. ### Claim 8 (depends on 7) The gas turbine engine according to claim 7, wherein the third bearing is a roller bearing or tapered roller bearing. ### Claim 9 (depends on 5) The gas turbine engine according to claim 5, wherein the second shaft is an intermediate pressure shaft. ### Claim 10 (depends on 1) The gas turbine engine according to claim 1, wherein the gas turbine engine is an aircraft engine with a geared turbofan arrangement.