Kühleinrichtung zum Abführen von Wärme von einer im Innenraum eines Flugzeuges angeordneten Wärmequelle

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...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	MARKWART, MICHAEL, MUEHLTHALER, GEORG
Format:	Patent
Sprache:	ger
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEAT EXCHANGE IN GENERAL HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT HEATING LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	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).