Cooling Device for Installation in an Aircraft

Abstract

The present invention relates to a cooling device ( 20 ) for installation in an aircraft, in particular a passenger aircraft. The cooling device ( 20 ) comprises a heat exchanger ( 26 ) configured for flow-through of a liquid coolant for pre-cooling a cooling chamber ( 34 ) of the cooling device ( 20 ) to a temperature of the liquid coolant, the heat exchanger ( 26 ) being coupled in a heat-transferring manner to a refrigerant ( 28 ) which is in thermal contact with the cooling chamber ( 34 ) of the cooling device ( 20 ) for cooling the cooling chamber ( 34 ) to a temperature which is below the temperature of the liquid coolant, wherein the heat exchanger ( 26 ) and the refrigerant ( 28 ) are disposed inside the cooling chamber ( 34 ) of the cooling device ( 20 ), and wherein the heat exchanger ( 26 ) is configured for connection to a liquid coolant supply system installed on board the aircraft.

1 - 10 . (canceled) 
     
     
         11 . Cooling device ( 20 ) for installation in an aircraft, in particular a passenger aircraft, comprising a heat exchanger ( 26 ) configured for flow-through of a liquid coolant for pre-cooling a cooling chamber ( 34 ) of the cooling device ( 20 ) to a temperature of the liquid coolant, the heat exchanger ( 26 ) being coupled in a heat-transferring manner to a refrigerant ( 28 ) which is in thermal contact with the cooling chamber ( 34 ) of the cooling device ( 20 ) for cooling the cooling chamber ( 34 ) to a temperature which is below the temperature of the liquid coolant, wherein the beat exchanger ( 26 ) and the refrigerant ( 28 ) are disposed inside the cooling chamber ( 34 ) of the cooling device ( 20 ), and wherein the heat exchanger ( 26 ) is configured for connection to a liquid coolant supply system installed on board the aircraft. 
     
     
         12 . Cooling device according to  claim 11 , wherein the refrigerant ( 28 ) is a Peltier element. 
     
     
         13 . Cooling device according to  claim 11 , wherein that the heat exchanger ( 26 ) is provided with an intake ( 22 ) and a return ( 24 ) for the liquid coolant for connection to a line system which is installed on board the aircraft. 
     
     
         14 . Cooling device according to  claim 11 , wherein the heat exchanger ( 26 ) is configured according to the counterflow principle. 
     
     
         15 . Cooling device according to  claim 11 , wherein the heat exchanger ( 26 ) comprises a throttle element ( 32 ) for throttling the flow volume of the liquid coolant through the heat exchanger ( 26 ). 
     
     
         16 . Cooling device according to  claim 15 , wherein the throttle element ( 32 ) is a control valve. 
     
     
         17 . Cooling device according to  claim 11 , wherein the heat exchanger ( 26 ) is provided with an intake ( 22 ) and a return ( 24 ) for the liquid coolant for connection to a line system which is installed on board the aircraft, the heat exchanger ( 26 ) further comprising a throttle element ( 32 ) for throttling the flow volume of the liquid coolant through the heat exchanger ( 26 ), wherein the throttle element ( 32 ) is disposed in the return ( 24 ). 
     
     
         18 . Cooling device according to  claim 17 , wherein the throttle element ( 32 ) is a control valve. 
     
     
         19 . Cooling device according to  claim 11 , wherein a fan ( 30 ) is disposed in the cooling chamber ( 34 ). 
     
     
         20 . Cooling device according to  claim 11 , wherein the liquid coolant does not undergo a phase transition during operation of the cooling device. 
     
     
         21 . Cooling device according to  claim 11 , wherein the heat exchanger ( 26 ) and the refrigerant ( 28 ) are configured such that the cooling chamber ( 34 ) can be cooled to a temperature below 0° Celsius.