# US 8,739,516 B2 · Turboreactor for aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,739,516 B2 - Document ID: US8739516B2 - Status: Granted - Kind: B2 - Application number: 12/306,177 - Filed: 2007-06-19 - Published: 2009-12-10 - Granted: 2014-06-03 - Earliest claimed: 2006-06-27 - Assignees: Airbus Operations GmbH - Applicants: Guillaume Bulin; Patrick Oberle - Inventors: Guillaume Bulin; Patrick Oberle - Web page: https://patentgrep.com/patent/US8739516B2 ## CPC - F02K 3/04: the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type - F02C 7/14: of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} - F05D 2240/14: Casings or housings protecting or supporting assemblies within - F05D 2260/20: Heat transfer, e.g. cooling - F28D 2021/0021: {for aircrafts or cosmonautics} - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - F28D: HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT (fluid heaters having heat generating means and heat transferring means F24H; furnaces F27; details of heat-exchange apparatus of general) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet. ## Claims ### Claim 1 A turbojet for an aircraft including an engine located in a nacelle the turbojet comprising: a thermal exchanger adapted to cool a liquid participating in the engine propulsive system, wherein said thermal exchanger is located downstream from the nacelle and at a surface level of an external wall of the engine, an interstitial space being defined in a recess, the recess receiving the thermal exchanger in a disposition wherein air can circulate in the interstitial space between an engine external wall and an inner wall of said thermal exchanger, wherein the interstitial space is defined by an intake opening, adjoining a shallow in-slope portion, adjoining a steep in-slope portion, adjoining an arcuate bottom portion, adjoining a steep out-slope portion, adjoining a portion substantially parallel to the axis of the engine, adjoining a shallow out-slope portion, adjoining an exhaust opening, thereby creating a thermal resistance between the engine external wall and the inner wall of said thermal exchanger. ### Claim 2 (depends on 1) The turbojet according to claim 1, wherein the turbojet includes an attaching strut assembly adapted to attach the thermal exchanger to the engine external wall. ### Claim 3 (depends on 2) The turbojet according to claim 2, wherein the attaching strut assembly include at least one strut. ### Claim 4 (depends on 1) The turbojet according to claim 1, wherein the interstitial space forms an air pocket. ### Claim 5 (depends on 1) The turbojet according to claim 1, wherein the engine external wall includes a recess formed therein for receiving at least a portion of the thermal exchanger in a spaced apart disposition. ### Claim 6 (depends on 1) The turbojet according to claim 1, wherein the thermal exchanger is provided with an air inlet, positioned upstream from the thermal exchanger, and adapted to admit air to the interstitial space. ### Claim 7 (depends on 6) The turbojet according to claim 6, wherein the air inlet receives air from a secondary air flow, the secondary air flow passing through the nacelle. ### Claim 8 (depends on 1) The turbojet according to claim 1, wherein the thermal exchanger includes an air outlet positioned downstream from a thermal exchanger body, and adapted to exhaust the air circulating in the interstitial space out of aforesaid interstitial space. ### Claim 9 (depends on 1) The turbojet according to claim 1, wherein the thermal exchanger is positioned circumferentially around the engine. ### Claim 10 An aircraft including at least one turbojet for the aircraft, the at least one turbojet including an engine located in a nacelle, the aircraft comprising: a thermal exchanger adapted to cool a liquid participating in the engine propulsive system, wherein said thermal exchanger is located downstream from the nacelle and at a surface level of an external wall of the engine, an interstitial space being defined in a recess, the recess receiving the thermal exchanger in a disposition wherein air can circulate in the interstitial space between an engine external wall and an inner wall of said thermal exchanger, wherein the interstitial space is defined by an intake opening, adjoining a shallow in-slope portion, adjoining a steep in-slope portion, adjoining an arcuate bottom portion, adjoining a steep out-slope portion, adjoining a portion substantially parallel to the axis of the engine, adjoining a shallow out-slope portion, adjoining an exhaust opening, thereby creating a thermal resistance between the engine external wall and the inner wall of said thermal exchanger. ### Claim 11 (depends on 1) The turbojet according to claim 1, wherein the openings are at a surface level of the external wall of the engine to reduce aerodynamic drag. ### Claim 12 (depends on 1) The turbojet according to claim 1, wherein the openings are formed as slots extending the whole width of thermal exchanger. ### Claim 13 (depends on 1) The turbojet according to claim 1, wherein the interstitial space is in fluid communication with two or more openings upstream and two or more openings downstream of the interstitial space, the upstream and downstream openings symmetrical to one another. ### Claim 14 (depends on 1) The turbojet according to claim 1, wherein the at least one opening upstream is a punctual air inlet. ### Claim 15 (depends on 1) The turbojet according to claim 1, wherein a bottle neck is formed within the interstitial space. ### Claim 16 (depends on 1) The turbojet according to claim 1, wherein air circulation between the engine external wall and the inner wall of said thermal exchanger is regulated by one or more valves. ### Claim 17 A turbojet engine for an aircraft comprising: a motor housed in a nacelle, wherein an internal wall of the nacelle and an external wall of the motor is at least partially covered with an acoustic coating; and a thermal exchanger adapted to cool a fluid participating in the propulsion system of the motor, wherein said thermal exchanger is located downstream from the acoustic coating and at a surface level of the external wall of the motor, an interstitial space being defined in a recess, the recess receiving the thermal exchanger in a disposition wherein air can circulate in the interstitial space between an motor external wall and an inner wall of said thermal exchanger, wherein the interstitial space is defined by an intake opening, adjoining a shallow in-slope portion, adjoining a steep in-slope portion, adjoining an arcuate bottom portion, adjoining a steep out-slope portion, adjoining a portion substantially parallel to the axis of the engine, adjoining a shallow out-slope portion, adjoining an exhaust opening, thereby creating a thermal resistance between the motor external wall and the inner wall of said thermal exchanger.