# US 10,119,477 B2 · Gas turbine engine with a multi-spool driven fan > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,119,477 B2 - Document ID: US10119477B2 - Status: Granted - Kind: B2 - Application number: 14/600,978 - Filed: 2015-01-20 - Published: 2016-07-21 - Granted: 2018-11-06 - Earliest claimed: 2015-01-20 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Christopher J. Hanlon; Daniel B. Kupratis; Walter A. Ledwith - Web page: https://patentgrep.com/patent/US10119477B2 ## CPC - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F02K 3/075: controlling flow ratio between flows - F02K 3/077: the plant being of the multiple flow type, i.e. having three or more flows - 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) - 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) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine includes low and high spools constructed and arranged to rotate about an engine axis. The low spool drives at least one leading stage of a fan section and the high spool drives an aft stage of the fan section. The aft stage may generally include a bypass duct for controllably flowing a bypass stream directly from the leading stage and controllably and/or selectively into an auxiliary flowpath and/or into a second flowpath both located radially outward from a core flowpath. ## Claims ### Claim 1 A gas turbine engine comprising: a high spool constructed and arranged to rotate about an engine axis; a low spool constructed and arranged to rotate about the engine axis; a fan leading stage connected for rotation to the low spool; a fan aft stage connected for rotation to the high spool; a fan outer housing axially aligned to and circumferentially surrounding the leading and aft stages; a fan inner housing spaced radially inward from the outer housing, located aft of the leading stage, and circumferentially surrounding the aft stage, wherein a bypass duct is defined by and radially between the outer housing and the inner housing for at least partially flowing air from the leading stage; a core case concentrically located about the engine axis, wherein a core flowpath is defined radially inward of the core case for flowing a core stream; a second case spaced radially outward of the core case, wherein a second flowpath is defined radially between the core and second case for flowing a second stream; and an outer case spaced at least in-part radially outward from the second case, wherein an auxiliary flowpath is defined at least in-part radially between the second and outer cases for flowing an auxiliary stream; wherein the bypass duct is in selective, direct communication with the second flowpath and the auxiliary flowpath such that air in the bypass duct is provided alternatively into the auxiliary flowpath or the second flowpath. ### Claim 2 (depends on 1) The gas turbine engine set forth in claim 1 further comprising: a high pressure turbine connected to the high spool. ### Claim 3 (depends on 2) The gas turbine engine set forth in claim 2 further comprising: a low pressure turbine connected to the low spool. ### Claim 4 (depends on 1) The gas turbine engine set forth in claim 1 further comprising: a control valve arrangement constructed and arranged to control airflow from the bypass duct to the second flowpath. ### Claim 5 (depends on 4) The gas turbine engine set forth in claim 4, wherein the control valve arrangement includes an isolation valve feature to selectively prevent flow through the bypass duct. ### Claim 6 (depends on 5) The gas turbine engine set forth in claim 5, Wherein the control valve arrangement includes a selector valve feature for controllably diverting airflow between the auxiliary and second flowpaths. ### Claim 7 (depends on 1) The gas turbine engine set forth in claim 1, further comprising: an airflow control system including at least one heat exchanging device arranged to heat a portion of the second stream from the second flowpath upon entry into the auxiliary flow/path. ### Claim 8 (depends on 7) The gas turbine engine set forth in claim 7, wherein the at least one heat exchanging device includes a heat exchanger and a control valve constructed and arranged to control flow through the heat exchanger. ### Claim 9 (depends on 8) The gas turbine engine set forth in claim 8 further comprising: a control valve arrangement constructed and arranged to control airflow from the bypass duct to the second flowpath, and wherein the airflow control system includes a controller constructed and arranged to control the control valve arrangement and the control valve of the heat exchanging device. ### Claim 10 (depends on 7) The gas turbine engine set forth in claim 7, wherein the heat exchanging device includes a conduit loop in direct fluid communication between the core flowpath and a hot side of the heat exchanger for flowing heated air from the core flowpath to the hot side and returning the cooled hot air from the hot side and through the core case for cooling components within the core case, and wherein a cold side of the heat exchanger is constructed and arranged to flow the portion of the second stream for cooling the hot air. ### Claim 11 (depends on 1) The gas turbine engine of claim 1, wherein air flowing within the bypass duct is operable to flow out of the bypass duct into at least the second flowpath during a first mode; and the air flowing with the bypass duct is operable to flow out of the bypass duct into at least the auxiliary flowpath during a second mode. ### Claim 12 A gas turbine engine comprising: a low pressure turbine; a high pressure turbine proximate to the low pressure turbine; a first fan stage driven by the low pressure turbine and comprising a first fan blade, wherein the first fan blade includes a first airfoil that extends in span to a tip of the first fan blade; a second fan stage driven by the high pressure turbine and comprising a second fan blade, wherein the second fan blade includes a second airfoil that extends in span to a tip of the second fan blade, and the second airfoil is operable to receive air propelled by the first airfoil; a core flowpath through an engine core downstream of the second fan stage; a second flowpath radially outside of and surrounding the core flowpath; and an auxiliary flowpath radially outside of and surrounding the core flowpath and the second flowpath; wherein the second fan stage includes a bypass duct in direct, selective, communication between the auxiliary flowpath and the second flowpath, and the bypass duct is adapted to direct a bypass flow at least partially into the auxiliary flowpath, independent of the second flowpath, during a first mode of gas turbine engine operation; and at least partially into the second flowpath, independent of the auxiliary flowpath, during a second mode of gas turbine engine operation and wherein the bypass duct circumscribes the second fan blade such that air in the bypass duct bypasses the second fan stage. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein air flowing within the second flowpath is operable to flow out of the second flowpath and into at least the auxiliary flowpath during a third mode of gas turbine engine operation. ### Claim 14 (depends on 12) The gas turbine engine of claim 12, wherein a first portion of the second flowpath is upstream of a fluid coupling between the second flowpath and the bypass duct, and a second portion of the second flowpath is downstream of the fluid coupling between the second flowpath and the bypass duct. ### Claim 15 A method of operating a gas turbine engine comprising the steps of: driving a leading stage of a fan section with a low spool; driving an aft stage of a fan section with a high spool; directing air from the leading stage to a bypass duct and to the aft stage, wherein the bypass duct circumscribes the aft stage of the fan section such that air in the bypass duct bypasses the second fan stage; directing air from the aft stage to a core flowpath through an engine core and a second flowpath that is radially outboard of and surrounding the core flowpath; controlling a valve arrangement to divert air flowing within the bypass duct out of the bypass duct and into the second flowpath during a first mode; and controlling the valve arrangement to divert air flowing within the second flowpath out of the second flowpath and into an auxiliary flowpath during a second mode, wherein the auxiliary flowpath is downstream of the bypass duct and radially outboard of and surrounding the second flowpath. ### Claim 16 (depends on 15) The method set forth in claim 15 comprising the further step of utilizing a flow control system to controllably flow at least a portion of the air directed by the leading stage through the aft stage. ### Claim 17 (depends on 15) The method set forth in claim 15 comprising the further step of: controlling the valve arrangement with a controller to control a flow of a bypass stream through the bypass duct.