MULTIPLE STREAM HEAT EXCHANGER

A thermal management system (62) for a gas turbine engine (20) includes a heat exchanger (78) including a first coolant passage (86) for a first coolant medium and a second coolant passage (88) for a second coolant medium that is different than the first coolant medium. A first hot flow passage (90)...

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Bibliographische Detailangaben
1. Verfasser:	RIBAROV, Lubomir A
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING 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-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 MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A thermal management system (62) for a gas turbine engine (20) includes a heat exchanger (78) including a first coolant passage (86) for a first coolant medium and a second coolant passage (88) for a second coolant medium that is different than the first coolant medium. A first hot flow passage (90) is in thermal communication with the first coolant passage (86). A second hot flow passage (92) is in thermal communication with the second coolant passage (88) all within a common housing (80). A first valve (108) controls a flow of a hot medium into at least one of the first hot flow passage (90) or the second hot flow passage (92). A controller (25) configured to operate the first valve (108) to direct the flow of hot medium into one of the first hot flow passage (90) and the second hot flow passage (92) for transferring thermal energy from the flow of hot medium into one of the first coolant medium and the second coolant medium.