# US 2016/0258359 A1 · Diversion Of Fan Air To Provide Cooling Air For Gas Turbine Engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2016/0258359 A1 - Document ID: US20160258359A1 - Status: Published application - Kind: A1 - Application number: 14/635,366 - Filed: 2015-03-02 - Published: 2016-09-08 - Earliest claimed: 2015-03-02 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Daniel Bernard Kupratis; Anthony R. Bifulco - Web page: https://patentgrep.com/patent/US20160258359A1 ## CPC - F02C 7/143: before or between the compressor stages - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F02C 3/13: having variable working fluid interconnections between turbines or compressors or stages of different rotors {(controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075)} - F02C 3/32: Inducing air flow by fluid jet, e.g. ejector action - F02C 7/10: by means of regenerative heat-exchangers - F02C 7/12: Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2260/14: Preswirling - F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes - F05D 2260/232: characterized by the cooling medium - F05D 2260/601: using an ejector or a jet pump - 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) - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages. ## Claims ### Claim 1 A gas turbine engine section comprising: a plurality of spaced rotor stages, with a static guide vane intermediate said spaced rotor stages, said static guide vane providing swirl into air passing toward a downstream one of said spaced rotor stages, and an outer housing surrounding said spaced rotor stages, a diverter diverting a portion of air radially outwardly through said outer housing, and across at least one heat exchanger, with the diverted air passing back into a duct radially inwardly through said outer housing, and being exhausted toward said downstream one of said spaced rotor stages. ### Claim 2 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said exhausted air passing through an injector. ### Claim 3 (depends on 2) The gas turbine engine as set forth in claim 2, wherein said injector imparting swirl into the air exhausting toward the downstream one of the two spaced turbine rotors. ### Claim 4 (depends on 3) The gas turbine engine as set forth in claim 3, wherein a swirl angle imparted by said injector is greater than a swirl angle imparted by said static guide vane. ### Claim 5 (depends on 4) The gas turbine engine as set forth in claim 4, wherein a swirl angle imparted by said static guide vane is greater than 40 degrees. ### Claim 6 (depends on 5) The gas turbine engine as set forth in claim 5, wherein said swirl angle is greater than 55 degrees. ### Claim 7 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said at least one heat exchanger cooling an electronic component. ### Claim 8 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said at least one heat exchanger cooling air from a compressor rotor. ### Claim 9 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said spaced rotor stages are fan rotors. ### Claim 10 (depends on 9) The gas turbine engine as set forth in claim 9, wherein a swirl angle imparted by said static guide vane is greater than 40 degrees. ### Claim 11 (depends on 10) The gas turbine engine as set forth in claim 10, wherein said swirl angle is greater than 55 degrees. ### Claim 12 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said spaced rotor stages are compressor rotors. ### Claim 13 (depends on 12) The gas turbine engine as set forth in claim 12, wherein a swirl angle imparted by said static guide vane is greater than 40 degrees. ### Claim 14 (depends on 1) The gas turbine engine as set forth in claim 1, wherein a bypass housing surrounds said outer housing and said at least one heat exchanger being positioned within a flow path in said bypass housing. ### Claim 15 (depends on 14) The gas turbine engine as set forth in claim 14, wherein air in said flow path cools said at least one heat exchanger. ### Claim 16 (depends on 1) The gas turbine engine as set forth in claim 1, wherein there are a plurality of heat exchangers. ### Claim 17 (depends on 1) The gas turbine engine as set forth in claim 1, wherein a swirl angle imparted by said static guide vane is greater than 40 degrees. ### Claim 18 (depends on 17) The gas turbine engine as set forth in claim 17, wherein said swirl angle is greater than 55 degrees. ### Claim 19 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said portion of air diverted radially outwardly passes through a duct, and said duct extending generally axially in one direction, then being turned back in an opposed direction before passing radially inwardly and being exhausted. ### Claim 20 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said portion of air diverted radially outwardly passes into a duct which extends circumferentially around a center axis of said engine before being directed radially inwardly and being exhausted.