# US 10,119,475 B2 · Gas turbine engine geared architecture > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,119,475 B2 - Document ID: US10119475B2 - Status: Granted - Kind: B2 - Application number: 14/767,050 - Filed: 2014-01-24 - Published: 2015-12-31 - Granted: 2018-11-06 - Earliest claimed: 2013-02-13 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Gary D. Roberge - Web page: https://patentgrep.com/patent/US10119475B2 ## 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 3/073: the compressor and turbine stages being concentric - 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) ## Abstract A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan. ## Claims ### Claim 1 A gas turbine engine assembly comprising: a geared architecture that rotatably couples a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan; wherein the turbine is a high pressure turbine, and the geared architecture is a first geared architecture; and a second geared architecture rotatably coupled to the fan to rotate the fan at a different speed than a spool that drives the fan. ### Claim 2 (depends on 1) The gas turbine engine assembly of claim 1, wherein the first geared architecture is axially upstream from the compressor relative to a direction of flow through the engine. ### Claim 3 (depends on 2) The gas turbine engine assembly of claim 2, wherein the second geared architecture is axially upstream from the compressor relative to the direction of flow through the engine, and the high pressure turbine directly drives a high pressure compressor. ### Claim 4 (depends on 3) The gas turbine engine assembly of claim 3, wherein the compressor is a low pressure compressor. ### Claim 5 (depends on 1) The gas turbine engine assembly of claim 1, wherein the engine has a three spool architecture. ### Claim 6 (depends on 1) The gas turbine engine assembly of claim 1, wherein the high pressure turbine is rotatably coupled to a high pressure compressor. ### Claim 7 (depends on 1) The gas turbine engine assembly of claim 1, wherein the engine has a three spool architecture. ### Claim 8 (depends on 1) The gas turbine engine of claim 1, further comprising a low pressure turbine that is rotatably coupled to the fan through the second geared architecture. ### Claim 9 (depends on 1) The gas turbine engine assembly of claim 1, wherein the compressor is an intermediate compressor. ### Claim 10 A gas turbine engine assembly comprising: a fan section; a turbine section including a high pressure turbine; a compressor section including a high pressure compressor and a first compressor upstream of the high pressure compressor; wherein the high pressure turbine rotatably drives the high pressure compressor; and a geared architecture rotatably coupling the first compressor and the high pressure turbine to drive the first compressor at a different rotational speed than the high pressure turbine; and wherein the geared architecture is a first geared architecture, and further including a second geared architecture rotatably coupled to the fan section to rotate the fan section at a different speed than a spool driving the fan section. ### Claim 11 (depends on 10) The gas turbine engine of claim 10, wherein the engine has a three spool architecture. ### Claim 12 (depends on 10) The gas turbine engine assembly of claim 10, wherein the engine has a three spool architecture, and the first compressor is an intermediate compressor that is downstream of a low pressure compressor. ### Claim 13 (depends on 10) The gas turbine engine of claim 10, wherein the first compressor is a low pressure compressor. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the fan section includes a fan having less than 20 fan blades, the turbine section includes a low pressure turbine that drives the spool, and the low pressure turbine has no more than 6 turbine rotors such that a ratio between a total number of the fan blades and a total number of the turbine rotors is between 3.3 and 8.6. ### Claim 15 (depends on 14) The gas turbine engine of claim 14, further comprising a bypass ratio of greater than 10, and a low fan pressure ratio of less than 1.45, measured across the fan blade alone. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the high pressure turbine directly drives the high pressure compressor. ### Claim 17 (depends on 16) The gas turbine engine of claim 16, further comprising a mid-turbine frame between the low pressure turbine and the high pressure turbine, and the mid-turbine frame supports a bearing system and includes vanes in a core flow path upstream of the low pressure turbine.