# US 2014/0155213 A1 · Geared architecture gas turbine engine with improved lubrication and misalignment tolerant roller bearing system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0155213 A1 - Document ID: US20140155213A1 - Status: Published application - Kind: A1 - Application number: 13/691,171 - Filed: 2012-11-30 - Published: 2014-06-05 - Earliest claimed: 2012-11-30 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: William G. Sheridan - Web page: https://patentgrep.com/patent/US20140155213A1 ## 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) - F02C 3/107: with two or more rotors connected by power transmission - F02K 3/06: with front fan - F16H 57/0421: {on or within the casing, e.g. shields or baffles for collecting lubricant, tubes, pipes, grooves, channels or the like} - F16H 57/0456: {Lubrication by injection; Injection nozzles or tubes therefor (oil mist or spray lubrication F16H57/0458)} - F16H 57/0479: {Gears or bearings on planet carriers} - 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) - 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 A gas turbine engine includes a structural oil baffle housing which at least partially supports a set of intermediate gears. ## Claims ### Claim 1 A gas turbine engine, comprising: a geared architecture with a multiple of intermediate gears; and a structural oil baffle housing that at least partially supports said set of intermediate gears. ### Claim 2 (depends on 1) The gas turbine engine as recited in claim 1, wherein each of said multiple of intermediate gears is mounted to a respective flexible carrier post. ### Claim 3 (depends on 2) The gas turbine engine as recited in claim 2, further comprising a spherical joint mounted to each flexible carrier post. ### Claim 4 (depends on 2) The gas turbine engine as recited in claim 2, wherein said structural oil baffle housing is mounted to a spherical joint mounted to each flexible carrier post. ### Claim 5 (depends on 1) The gas turbine engine as recited in claim 1, further comprising a rotationally fixed carrier, each of said multiple of intermediate gears mounted to a respective flexible carrier post which extends from said carrier. ### Claim 6 (depends on 5) The gas turbine engine as recited in claim 5, further comprising an oil manifold defined by said carrier. ### Claim 7 (depends on 6) The gas turbine engine as recited in claim 6, wherein said oil manifold includes a first oil circuit and a second oil circuit. ### Claim 8 (depends on 7) The gas turbine engine as recited in claim 7, wherein said first oil circuit communicates with each respective flexible carrier post. ### Claim 9 (depends on 7) The gas turbine engine as recited in claim 7, wherein said second oil circuit communicates with a multiple of oil nozzles. ### Claim 10 (depends on 1) The gas turbine engine as recited in claim 1, further comprising a rolling element bearing mounted between said structural oil baffle housing and each of said multiple of intermediate gears. ### Claim 11 (depends on 10) The gas turbine engine as recited in claim 10, wherein said structural oil baffle housing directs oil to said multiple of intermediate gears. ### Claim 12 (depends on 1) The gas turbine engine as recited in claim 1, wherein said geared architecture includes a planetary gear system. ### Claim 13 (depends on 1) The gas turbine engine as recited in claim 1, wherein said geared architecture includes a star gear system. ### Claim 14 A gas turbine engine, comprising: a carrier which defines an oil manifold with a first oil circuit and a second oil circuit; a multiple of flexible carrier post which extends from said carrier to support a respective intermediate gear, said first oil circuit communicates with each respective flexible carrier post; a structural oil baffle housing which at least partially supports said set of intermediate gears; and a multiple of oil nozzles in communication with said second oil circuit. ### Claim 15 (depends on 10) The gas turbine engine as recited in claim 10, wherein said multiple of oil nozzles are external to said structural oil baffle housing. ### Claim 16 (depends on 15) The gas turbine engine as recited in claim 15, wherein said multiple of oil nozzles are each adjacent to a sun gear and one of said multiple of intermediate gears. ### Claim 17 (depends on 14) The gas turbine engine as recited in claim 14, further comprising a rolling element bearing mounted between said structural oil baffle housing and each of said multiple of intermediate gears. ### Claim 18 (depends on 17) The gas turbine engine as recited in claim 17, wherein said rolling element bearing is a ball bearing. ### Claim 19 (depends on 17) The gas turbine engine as recited in claim 17, wherein said rolling element bearing is a roller bearing.