A thermal management system (20) for an aircraft is provided. The thermal management system (20) may comprise a first vapor compression circuit (44), a second vapor compression circuit (46), and an intercooler (58). The first vapor compression circuit (44) may define a first flowpath for fluid compression, condensation, expansion, and evaporation. The second vapor compression circuit (46) may define a second flowpath for fluid compression, condensation, expansion, and evaporation. The intercooler (58) may be disposed in cascading thermal communication between the first vapor compression circuit (44) and the second vapor compression circuit (46). Generally, heat generated by the aircraft may be transferred to the first vapor compression circuit (44) during aircraft operation.
AIRCRAFT THERMAL MANAGEMENT SYSTEM
FLUGZEUGWÄRMEVERWALTUNGSSYSTEM
SYSTÈME DE GESTION THERMIQUE D'UN AÉRONEF
2017-08-02
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Thermal management system, aircraft and aircraft thermal management method
Europäisches Patentamt | 2023
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