An environmental control system of an aircraft includes at least one heat exchanger (70) and a compression device (60) arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component (62) and a second component (64) coupled by a shaft (68). A first bleed port (38) is arranged in fluid communication with the first component and a second bleed port (40), distinct from the first bleed port, is arranged in fluid communication with the second component.
SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM
SIMULTANES DUAL-BLEED SYSTEM FÜR EIN WÄRMEMANAGEMENTSYSTEM
SYSTÈME DE GESTION THERMIQUE AVEC DEUX CIRCUITS DE PRÉLÈVEMENT D'AIR MOTEUR SIMULTANÉS
2023-04-12
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Simultaneous dual engine bleed thermal management system
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