A environmental control system (ECS) for an aircraft includes a primary heat exchanger configured to receive bleed air from a turbine compressor of the aircraft and a secondary heat exchanger having an input configured to receive a flow from the primary heat exchanger and a secondary heat exchanger output. The ECS also includes a thermoelectric condensing device having an input in fluid communication with the output of the secondary heat exchanger and also having a thermoelectric condensing device output.
AIRCRAFT AIR CONDITIONING SYSTEM INCLUDING A THERMOELECTRIC DEVICE
2017-10-05
Patent
Elektronische Ressource
Englisch
AIRCRAFT AIR CONDITIONING SYSTEM INCLUDING A THERMOELECTRIC DEVICE
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