METHOD FOR COOLING ELECTRONIC COMPONENTS IN AN AIRCRAFT TURBOJET ENGINE

A method for cooling electronic components present in an aircraft turbojet engine, the method including disposing a first sensor in a first zone of the turbojet engine; disposing a second sensor in a second zone of the turbojet engine, the first zone and the second zone having a temperature gradient...

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Bibliographische Detailangaben
Hauptverfasser:	BALLAND MORGAN, FONTANEL EDDY, DAWSON LUCIE MATHILDE
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBINED HEATING AND REFRIGERATION SYSTEMS HEAT PUMP SYSTEMS HEATING LIGHTING LIQUEFACTION SOLIDIFICATION OF GASES MANUFACTURE OR STORAGE OF ICE MECHANICAL ENGINEERING REFRIGERATION MACHINES, PLANTS OR SYSTEMS REFRIGERATION OR COOLING WEAPONS
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Beschreibung
Zusammenfassung:	A method for cooling electronic components present in an aircraft turbojet engine, the method including disposing a first sensor in a first zone of the turbojet engine; disposing a second sensor in a second zone of the turbojet engine, the first zone and the second zone having a temperature gradient between them; generating, from the first sensor and the second sensor, electricity by the Seebeck effect; bringing about cooling of the electronic components by the Peltier effect, using the electricity generated by the Seebeck effect.