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.


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    Title :

    AIRCRAFT AIR CONDITIONING SYSTEM INCLUDING A THERMOELECTRIC DEVICE


    Contributors:

    Publication date :

    2017-10-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F25B Kältemaschinen, Kälteanlagen oder Kälteverfahren , REFRIGERATION MACHINES, PLANTS, OR SYSTEMS



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