Cooling system and method for expelling heat from a heat...

F - Mech Eng,Light,Heat,Weapons – 28 – D

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F28D 15/02 (2006.01) B64D 11/04 (2006.01) B64D 13/08 (2006.01)

Patent

CA 2552157

With a cooling system for expelling heat from a heat source (30) located in the interior of an aircraft to a heat reducer (32), with a piping system (10) sealed against the surrounding atmosphere which is thermally coupled to a heat intake section (14) with the heat source (38) and to a heat output section (22) with the heat reducer (32), and which preferably has an essentially adiabate transport section (21), it is proposed that the piping system (10) is filled with a heat conveyance medium (12) which, when taking in heat from the heat source (38) in the heat intake section (14) undergoes a transition from the liquid phase to the gaseous phase, then flows into the heat output section (22), and here, when discharging heat to the heat reducer (32) condenses once again, and flows back into the heat intake section (14).

L'invention concerne un système de tuyaux (10) rempli d'un milieu de transport de chaleur (12) subissant, lors du prélèvement de chaleur d'une source de chaleur (38) dans la section d'admission de chaleur (14), une transition de la phase liquide à la phase gazeuse, puis s'écoulant dans une section d'évacuation de chaleur (22) et lors de la décharge de la chaleur dans un réducteur de chaleur (332) se condensant à nouveau et retournant dans la section d'admission de chaleur (14), au moyen d'un système de refroidissement permettant d'évacuer la chaleur d'une source de chaleur (30) située à l'intérieur d'un aéronef vers le réducteur de chaleur (32), au moyen du système de tuyaux (10) scellé contre l'atmosphère ambiante et couplé thermiquement à la section d'admission de chaleur (14) avec la source de chaleur (38) et à la section d'évacuation de chaleur (22) avec le réducteur de chaleur (32) et comprenant, de préférence, une section de transport sensiblement adiabatique (21).

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