Patent ID: 8936071
Filing Date: 2015-01-20
Classification: B64D,Y02T,Y10S

Abstract:
1. An aircraft cooling system comprises: a refrigerant cycle, said refrigerant cycle including a first heat exchanger; a liquid cycle, said liquid cycle passing a liquid through said first heat exchanger, at which it is cooled by a refrigerant in the refrigerant cycle; an air cycle including a compressor for compressing air and delivering compressed air into a primary heat exchanger, and a fan to drive cooling air over said primary heat exchanger to cool the compressed air, the compressed air then being delivered into a second heat exchanger, and liquid passing through said second heat exchanger at a location downstream of said first heat exchanger, and the liquid for cooling the air in said second heat exchanger, air downstream of said second heat exchanger passing to be utilized by an air use on an aircraft; said air cycle includes a turbine downstream of said second heat exchanger, and air having been cooled in said second heat exchanger driving said turbine to expand the air, and at least partially power said compressor; a water extractor is positioned downstream of said second heat exchanger, and upstream of said turbine; a liquid supply line branches to at least two destinations downstream of said first heat exchanger, with one branch passing through said second heat exchanger, and another branch passing to a liquid use for cool liquid; and said air cycle includes a third heat exchanger downstream of said second heat exchanger, and a portion of the liquid which is not delivered to said second heat exchanger passing through said third heat exchanger prior to passing to the liquid use.