COOLING SYSTEM

A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes a plurality of heat source exchangers and at least one heat sink exchanger. The plurali...

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Bibliographische Detailangaben
Hauptverfasser:	MILLER, Brandon Wayne, KROGER, Christopher James, CERNY, Matthew Robert
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBINED HEATING AND REFRIGERATION SYSTEMS COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OFGENERAL APPLICATION GAS-TURBINE PLANTS HEAT EXCHANGE IN GENERAL HEAT PUMP SYSTEMS HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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 thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes a plurality of heat source exchangers and at least one heat sink exchanger. The plurality of heat source exchangers and the at least one heat sink exchanger are in thermal communication with the heat exchange fluid in the thermal transport bus. The plurality of heat source exchangers are arranged along the thermal transport bus and configured to transfer heat from one or more accessory systems to the heat exchange fluid, and the at least one heat sink exchanger is located downstream of the plurality of heat source exchangers and configured to remove heat from the heat exchange fluid.