Heat management system for aircraft
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorArnold H. Mayer
Life of this patent
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Abstract
A novel heat management system for aircraft is provided which is based on the aircraft fuel as the heat exchange medium and comprises a dedicated thermal reserve fuel tank for containing refrigerated aircraft fuel (or other expendable liquid) which is cooled by heat exchange with the primary aircraft fuel flow to the engines, a fuel line loop for conducting fuel through a plurality of heat exchangers associated with cooling loops for heat generating aircraft systems, and a central microprocessor based controller for controlling fuel flow and temperature throughout the fuel loop system and into the aircraft engine.
Claims13
A heat management system for an aircraft having an engine, a main fuel tank for storage and supply of fuel for said engine, a first fuel line through which fuel is supplied from said main fuel tank to said engine for consumption therein, and a main fuel pump for pumping said fuel from said main fuel tank to said engine through said first fuel line, comprising:
- a. a cooling loop thermally interfacing the fuel flow through said first fuel line for extracting heat from the fuel contained in said main fuel tank by circulation of a refrigerant through said loop, said loop including a condenser near said first fuel line intermediate said main fuel pump and said engine, said condenser thermally interfacing the fuel flow through said first fuel line, an evaporator near said main fuel tank and thermally interfacing the fuel contained therein, and a thermal expansion valve and compressor intermediate said condenser and evaporator for circulating said refrigerant through said loop;
- b. a second fuel line interconnecting said main fuel tank with said first fuel line at a point intermediate said condenser and said engine, for recirculating to said main fuel tank fuel flowing through said first fuel line in excess of momentaneous engine consumption requirements;
- and
- c. a first control valve for controlling the flow of fuel through said second fuel line.
A heat management system for an aircraft having an engine, a main fuel tank for storage and supply of fuel for said engine, a first fuel line through which fuel is supplied from said main fuel tank to said engine for consumption therein, and a main fuel pump for pumping said fuel from said main fuel tank to said engine through said first fuel line, comprising:
- a. a reserve tank for containing cooled fuel;
- b. a cooling loop, thermally interfacing the fuel flow through said first fuel line, for extracting heat from the fuel contained in said reserve tank by circulation of a refrigerant through said loop, said loop including a condenser near said first fuel line intermediate said main fuel pump and said engine, said condenser thermally interfacing the fuel flow through said first fuel line, an evaporator near said reserve tank and thermally interfacing the fuel contained therein, and a thermal expansion valve and compressor intermediate said condenser and evaporator for circulating said refrigerant through said loop;
- c. a second fuel line interconnecting said main fuel tank with said first fuel line at a point intermediate said condenser and said engine, for recirculating to said main fuel tank fuel flowing through said fuel line in excess of momentaneous engine consumption requirements;
- and
- d. a first control valve for controlling the flow of fuel through said second fuel line.
Dependencies are inferred from the claim text.