# US 10,308,367 B2 · Systems for generating auxiliary electrical power for jet aircraft propulsion systems > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,308,367 B2 - Document ID: US10308367B2 - Status: Granted - Kind: B2 - Application number: 16/006,680 - Filed: 2018-06-12 - Published: 2018-10-11 - Granted: 2019-06-04 - Earliest claimed: 2013-09-16 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: John Akin - Web page: https://patentgrep.com/patent/US10308367B2 ## CPC - B64D 33/00: Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for - B64D 27/16: of jet type - F02C 7/00: Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) - H02K 7/1823: {structurally associated with turbines or similar engines} - H10N 10/13: characterised by the heat-exchanging means at the junction - H10N 10/80: Constructional details - B64D 2221/00: Electric power distribution systems onboard aircraft - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN 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) - H02K: DYNAMO-ELECTRIC MACHINES (dynamo-electric relays H01H53/00; conversion of DC or AC input power into surge output power {H03K3/53}) - H10N: ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An aircraft jet propulsion system is disclosed. The aircraft jet propulsion system may comprise a thermoelectric generator array (“TEG” array) coupled to a portion of the aircraft jet propulsion system, wherein the TEG array converts heat energy to electrical energy, and supplies power to the aircraft jet propulsion system, wherein the electrical energy is supplied to a power supply. The aircraft jet propulsion system may comprise an alternator that generates less energy than is required to power the aircraft jet propulsion system. The TEG array may supplement the energy generated by the alternator. The energy generated by the TEG array and the energy generated by the alternator may be sufficient to power the aircraft jet propulsion system and/or the electrical energy generated by the TEG array may be sufficient to power to aircraft jet propulsion system. ## Claims ### Claim 1 An aircraft jet propulsion system comprising: a first thermoelectric generator array (“TEG” array) coupled to an inner surface of a nacelle, wherein the first TEG array converts heat energy to electrical energy, wherein the electrical energy is supplied to the aircraft jet propulsion system. ### Claim 2 (depends on 1) The aircraft jet propulsion system of claim 1, further comprising an alternator that generates less energy than is associated with the electricity for operating the aircraft jet propulsion system. ### Claim 3 (depends on 2) The aircraft jet propulsion system of claim 2, wherein the first TEG array supplements the energy generated by the alternator. ### Claim 4 (depends on 3) The aircraft jet propulsion system of claim 3, wherein the energy generated by the first TEG array and the energy generated by the alternator are sufficient to electrically power the aircraft jet propulsion system. ### Claim 5 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the electrical energy generated by the first TEG array is sufficient to electrically power the aircraft jet propulsion system. ### Claim 6 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the first TEG array is coupled to an exhaust portion of the aircraft jet propulsion system. ### Claim 7 (depends on 6) The aircraft jet propulsion system of claim 6, wherein the exhaust portion is an exhaust nozzle. ### Claim 8 (depends on 1) The aircraft jet propulsion system of claim 1, further comprising a second TEG array coupled to an outer surface of an inner fixed structure (“IFS”). ### Claim 9 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the first TEG array is coupled between a heat blanket and the inner surface of the nacelle. ### Claim 10 (depends on 1) The aircraft jet propulsion system of claim 1, further comprising a second TEG array coupled to an air inlet. ### Claim 11 (depends on 10) The aircraft jet propulsion system of claim 10, wherein the second TEG array is coupled to an air inlet outboard of an anti-ice system. ### Claim 12 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the first TEG array comprises a plurality of thermoelectric generators (“TEGs”) electrically coupled in series. ### Claim 13 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the first TEG array comprises a plurality of sets of TEGs, each set electrically coupled in parallel. ### Claim 14 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the first TEG array comprises six sets of TEGs, each set electrically coupled in parallel. ### Claim 15 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the first TEG array comprises six TEGs coupled in series. ### Claim 16 (depends on 1) The aircraft jet propulsion system of claim 1, wherein the first TEG array generates approximately 28 Volts. ### Claim 17 A thermoelectric generator array (“TEG” array) comprising: a first set of thermoelectric generators (“TEGs”) coupled in series; and a second set of TEGs coupled in series, wherein the first set of TEGs and the second TEGs are coupled in parallel, wherein the TEG array recaptures heat energy generated by a turbofan engine and is coupled to an inner surface of a nacelle.