# US 9,752,510 B2 · Gas turbine engine driving multiple fans > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,752,510 B2 - Document ID: US9752510B2 - Status: Granted - Kind: B2 - Application number: 15/000,077 - Filed: 2016-01-19 - Published: 2016-05-12 - Granted: 2017-09-05 - Earliest claimed: 2012-02-29 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Gabriel L. Suciu; Alan H. Epstein; Wesley K. Lord; Michael E. McCune; Brian D. Merry - Web page: https://patentgrep.com/patent/US9752510B2 ## 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) - 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 - F05D 2220/32: in gas turbines - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2240/24: for turbines - F05D 2240/35: Combustors or associated equipment - F05D 2240/40: Use of a multiplicity of similar components - F05D 2240/60: Shafts - F05D 2260/4031: as in toothed gearing - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor. ## Claims ### Claim 1 A gas turbine engine comprising: a core engine including a compressor section, a combustor and a turbine, said turbine driving an output shaft; and said output shaft driving at least four gears, each of said at least four gears extending through a drive shaft to drive an associated fan rotor and said output shaft drives a pair of bevel gears, and each of said at least four gears being driven by at least one of said pair of bevel gears. ### Claim 2 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said pair of bevel gears rotate together, with each of said pair of bevel gears driving at least two of said at least four gears. ### Claim 3 (depends on 2) The gas turbine engine as set forth in claim 2, wherein said at least four gears are bevel gears. ### Claim 4 (depends on 3) The gas turbine engine as set forth in claim 3, wherein each drive shaft drives an output shaft bevel gear, and said output shaft bevel gear engages a fan rotor bevel gear which in turn drives one of the fan rotors. ### Claim 5 (depends on 4) The gas turbine engine as set forth in claim 4, wherein said output shaft also driving a fifth fan delivering air into the compressor section. ### Claim 6 (depends on 5) The gas turbine engine as set forth in claim 5, wherein said fifth fan is driven by a shaft upstream of said pair of bevel gears. ### Claim 7 (depends on 4) The gas turbine engine as set forth in claim 4, wherein each said output shaft is positioned upstream of the fan rotors. ### Claim 8 (depends on 4) The gas turbine engine as set forth in claim 4, wherein an exhaust of said core engine exhausts air through a duct, and an exhaust from said fan rotors is maintained substantially separate of said exhaust from said core engine. ### Claim 9 (depends on 8) The gas turbine engine as set forth in claim 8, wherein said exhaust of said core engine is positioned upstream of said fan rotors. ### Claim 10 (depends on 8) The gas turbine engine as set forth in claim 8, wherein said exhaust of said core engine is positioned downstream of said fan rotors. ### Claim 11 (depends on 1) The gas turbine engine as set forth in claim 1, wherein an exhaust of said core engine exhausts air through a duct, and an exhaust from said fan rotors is maintained substantially separate of said exhaust from said core engine. ### Claim 12 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said output shaft is positioned upstream of the fan rotors. ### Claim 13 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said output shaft also driving a fifth fan delivering air into the compressor section. ### Claim 14 (depends on 13) The gas turbine engine as set forth in claim 13, wherein said fifth fan is driven by a shaft upstream of said pair of bevel gears. ### Claim 15 (depends on 1) The gas turbine engine as set forth in claim 1, wherein each drive shaft drives an output shaft bevel gear, and said output shaft bevel gear engages a fan rotor bevel gear which in turn drives one of the fan rotors. ### Claim 16 (depends on 1) The gas turbine engine as set forth in claim 1, wherein an exhaust of said core engine is positioned upstream of said fan rotors. ### Claim 17 (depends on 1) The gas turbine engine as set forth in claim 1, wherein an exhaust of said core engine is positioned downstream of said fan rotors.