# US 11,994,069 B2 · System for cooling an aircraft turbojet engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,994,069 B2 - Document ID: US11994069B2 - Status: Granted - Kind: B2 - Application number: 17/490,766 - Filed: 2021-09-30 - Published: 2022-06-16 - Granted: 2024-05-28 - Earliest claimed: 2019-04-03 - Assignees: Safran Nacelles - Applicants: Safran Nacelles - Inventors: Julien Corbin; Jean-Nicolas Bouchout; Caroline Dang - Web page: https://patentgrep.com/patent/US11994069B2 ## CPC - F02C 7/14: of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F02K 1/56: Reversing jet main flow - F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow - F28F 9/26: Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators (connecting different sections in water heaters F24H9/14 {, connecting headers with inlet or outlet fittings F28F9/0246}) - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2250/41: with one degree of freedom - 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 2260/213: by the provision of a heat exchanger within the cooling circuit - F05D 2260/50: Kinematic linkage, i.e. transmission of position - F05D 2260/98: Lubrication - F28F 2265/26: for allowing differential expansion between elements - 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) - F28F: DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION (water and air traps, air venting F16) - 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 An engine nacelle, for a turbojet engine of the type having a lubricant, includes a cooling system. The cooling system includes a cold source heat-exchanger, configured to exchange heat between a heat-transfer fluid and air, a heat-transfer fluid inlet duct leading into the cold source heat-exchanger, and a heat-transfer fluid outlet duct leading out of the cold source heat-exchanger. The inlet and outlet ducts are configured to form a recirculation loop between the cold source heat-exchanger and a hot source heat-exchanger, configured to exchange heat between the heat-transfer fluid and the lubricant. The cold source heat-exchanger is arranged on a movable surface of the nacelle with respect to the hot source heat-exchanger and the heat-transfer fluid inlet and outlet ducts are extendable and/or flexible to permit the relative movement between the cold source heat-exchanger and the hot source heat-exchanger. ## Claims ### Claim 1 A nacelle for a turbojet engine, the nacelle comprising: an outer structure and an inner structure defining an annular flow path configured to direct a secondary air stream, the outer structure comprising an outer fairing defining an outer aerodynamic surface and an inner fairing defining an inner aerodynamic surface, the outer fairing and the inner fairing being connected upstream by a leading edge wall forming an air inlet lip; a thrust reverser; and a cooling system comprising: a first heat-exchanger configured to exchange heat between a heat-transfer fluid and a lubricant of the turbojet engine; a second heat-exchanger configured to exchange heat between the heat-transfer fluid and air; a heat-transfer fluid inlet conduit configured to permit the heat-transfer fluid to flow into the second heat-exchanger; and a heat-transfer fluid outlet conduit configured to permit the heat-transfer fluid to flow out of the second heat-exchanger, wherein the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit are configured to form a recirculation loop between the second heat-exchanger and the first heat-exchanger, wherein the second heat-exchanger is movable relative to the first heat-exchanger and is disposed in the thrust reverser, and the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit are extendable, flexible, or extendable and flexible to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger. ### Claim 2 (depends on 1) The nacelle according to claim 1, wherein the second heat-exchanger is a surface heat-exchanger. ### Claim 3 (depends on 2) The nacelle according to claim 2, wherein the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit comprise a deployable device configured to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger. ### Claim 4 (depends on 3) The nacelle according to claim 3, wherein the deployable device is a telescopic tube. ### Claim 5 (depends on 4) The nacelle according to claim 4, wherein the telescopic tube comprises several stages. ### Claim 6 (depends on 4) The nacelle according to claim 4, wherein the telescopic tube comprises one single stage. ### Claim 7 (depends on 3) The nacelle according to claim 3, wherein the deployable device is a bellow device. ### Claim 8 (depends on 7) The nacelle according to claim 7 further comprising a guide system configured to guide the movement of the bellow device. ### Claim 9 (depends on 8) The nacelle according to claim 8, wherein the guide system is a tube comprising at least two portions configured so as to slide into one another. ### Claim 10 (depends on 8) The nacelle according to claim 8, wherein the guide system includes a rail and a slide. ### Claim 11 (depends on 3) The nacelle according to claim 3, wherein the deployable device is a flexible conduit adapted to be wound on itself and to be unwound to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger. ### Claim 12 (depends on 1) The nacelle according to claim 1, wherein the second heat-exchanger is a structural heat-exchanger integral with the nacelle. ### Claim 13 (depends on 1) The nacelle according to claim 1, wherein the heat-transfer fluid inlet conduit and the heat-transfer fluid outlet conduit comprise a deployable device configured to accommodate the relative movement between the first heat-exchanger and the second heat-exchanger.