A environmental control system (ECS) for an aircraft includes a primary heat exchanger (220) configured to receive bleed air from a turbine compressor of the aircraft and a secondary heat exchanger (230) having an input configured to receive a flow from the primary heat exchanger (220) and a secondary heat exchanger (230) output. The ECS also includes a thermoelectric condensing device (202) having an input in fluid communication with the output of the secondary heat exchanger (230) and also having a thermoelectric condensing device (202) output.
AIRCRAFT AIR CONDITIONING SYSTEM INCLUDING A THERMOELECTRIC DEVICE
FLUGZEUGKLIMAANLAGENSYSTEM EINSCHLIESSLICH EINER THERMOELEKTRISCHEN VORRICHTUNG
SYSTÈME DE CLIMATISATION D'AÉRONEF COMPRENANT UN DISPOSITIF THERMOÉLECTRIQUE
2019-08-07
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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