DYNAMIC THERMAL LOAD MONITORING AND MITIGATION FOR AIRCRAFT SYSTEMS

A thermal management system (68) for a gas turbine engine (20) includes a cooler (70) including a first portion (72) and a second portion (74), the first portion (72) for cooling a hot flow (80) with a coolant (78) and the second portion (74) for cooling the coolant with a refrigerant (82). A vapor...

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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 GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A thermal management system (68) for a gas turbine engine (20) includes a cooler (70) including a first portion (72) and a second portion (74), the first portion (72) for cooling a hot flow (80) with a coolant (78) and the second portion (74) for cooling the coolant with a refrigerant (82). A vapor compression system (66) circulates the refrigerant (82) through the second portion of the cooler (70). The vapor compression system (66) is a closed system in communication with at least one heat load (76A-D) in addition to the second portion (74) of the cooler (70).