A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.


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    Title :

    ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS


    Additional title:

    ADAPTIVE TRANSKRITISCHE CO2-KÜHLSYSTEME FÜR LUFT- UND RAUMFAHRTANWENDUNGEN
    SYSTÈMES DE REFROIDISSEMENT DE CO2 TRANSCRITIQUES ADAPTATIFS POUR APPLICATIONS AÉROSPATIALES


    Contributors:

    Publication date :

    2020-03-25


    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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