Method for cooling electronic components in an aircraft turbojet engine

Abstract

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.

1 . A method for cooling an electronic component in an aircraft turbojet engine, the method comprising:
 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;   cooling the electronic component by the Peltier effect, using the electricity generated by the Seebeck effect.   
     
     
         2 . The method according to  claim 1 , comprising storing electrical energy, generated by the Seebeck effect, in a module capable of storing electrical energy, the stored electrical energy being used to cool the electronic component by the Peltier effect. 
     
     
         3 . The method according to  claim 1 , wherein the temperature gradient present between the first zone and the second zone of the turbojet engine is an axial temperature gradient. 
     
     
         4 . The method according to  claim 3 , wherein the first zone is a zone comprising a turbine of the turbojet engine, and wherein the second zone is a zone comprising a compressor of the turbojet engine. 
     
     
         5 . The method according to  claim 1 , wherein the temperature gradient present between the first zone and the second zone of the turbojet engine is a vertical temperature gradient. 
     
     
         6 . A method for cooling an electronic component in an aircraft engine, the method comprising:
 generating, using a first sensor and a second sensor, electricity by the Seebeck effect, the first sensor arranged in a first zone of the aircraft engine and the second sensor arranged in a second zone of the aircraft engine, the first zone and the second zone having a temperature gradient between them; and   cooling the electronic component by the Peltier effect, using the electricity generated by the Seebeck effect.   
     
     
         7 . The method according to  claim 6 , comprising storing electrical energy, generated by the Seebeck effect, in a module capable of storing electrical energy, the stored electrical energy being used to cool the electronic component by the Peltier effect. 
     
     
         8 . The method according to  claim 6 , wherein the aircraft engine is a turbojet engine. 
     
     
         9 . A cooling system for cooling an electronic component in an aircraft engine, the cooling system comprising:
 a first sensor arranged in a first zone of the aircraft engine;   a second sensor arranged in a second zone of the aircraft engine, the first zone and the second zone being spaced apart from each other so that a temperature gradient exists between the first and the second zone during use of the aircraft engine;   a module connected to each of said first and second sensors, said module adapted to store electricity generated by the Seebeck effect resulting from the temperature gradient between the first and second zones; and   a Peltier cell connected to said module and arranged to cool said electronic component using electricity stored in said module.   
     
     
         10 . The cooling system according to  claim 8 , wherein the first and second zones are located along a longitudinal axis of said aircraft engine. 
     
     
         11 . The cooling system according to  claim 8 , wherein the first and second zones are transverse to a longitudinal axis of said aircraft engine, 
     
     
         12 . An aircraft engine comprising:
 a cooling system configured to cool an electronic component in said aircraft engine, the cooling system comprising
 a first sensor arranged in a first zone of the aircraft engine; 
 a second sensor arranged in a second zone of the aircraft engine, the first zone and the second zone being spaced apart from each other so that a temperature gradient exists between the first and the second zone during use of the aircraft engine; 
 a module connected to each of said first and second sensors, said module adapted to store electricity generated by the Seebeck effect resulting from the temperature gradient between the first and second zones; and 
 a Peltier cell connected to said module and arranged to cool said electronic component using electricity stored in said module. 
   
     
     
         13 . The aircraft engine according to  claim 12 , wherein the first and second zones are located along a longitudinal axis of said aircraft engine. 
     
     
         14 . The aircraft engine according to  claim 12 , wherein the first and second zones are transverse to a longitudinal axis of said aircraft engine.