Heat-transfer fluid for a cooling system of an aircraft turbojet engine
AssigneeSafran Nacelles
InventorsVincent Peyron, Jean-Nicolas Bouchout
Life of this patent
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Abstract
In a cooling system of an aircraft turbojet engine surrounded by a nacelle, a heat-transfer fluid is circulated that is less flammable than a lubricant (H) for the turbojet engine and liquid at temperatures between −70° C. and +175° C., the heat-transfer fluid (C) being intended to circulate in a closed-circuit circulation duct including a first surface heat-exchanger between the heat-transfer fluid (C) and air (F), at the level of at least one of the outer fairing and the inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid (C) and the lubricant (H).
Claims13
A method, in a cooling system of an aircraft turbojet engine surrounded by a nacelle, comprising circulating a heat-transfer fluid less flammable than a turbojet engine lubricant, the heat-transfer fluid being liquid at temperatures between −70° C. and +175° C., the heat-transfer fluid circulating in a closed-circuit circulation duct comprising a first surface heat-exchanger between the heat-transfer fluid and air, the first surface heat-exchanger being disposed within range of at least one of an outer fairing and an inner fairing of the nacelle, and a second surface heat-exchanger between the heat-transfer fluid and the turbojet engine lubricant.
A cooling system of an aircraft turbojet engine, the aircraft turbojet engine being surrounded by a nacelle, wherein the cooling system comprises:
- a first surface heat-exchanger between a heat-transfer fluid and air, wherein the heat-transfer fluid is less flammable than a turbojet engine lubricant, and the heat-transfer fluid is liquid at temperatures between −70° C. and +175° C.;
- a second surface heat-exchanger between the heat-transfer fluid and a turbojet engine lubricant;
- and
- a closed-circuit circulation duct of the heat-transfer fluid.
Dependencies are inferred from the claim text.