An aircraft pneumatic system (1) including a pneumatic actuator (20) arranged to operate at a pressure value at least equal to a pressure threshold, a line (30) fluidly connected between a pneumatic source (10) and the pneumatic actuator (20), and a venturi (40) disposed upstream of the line (30) and downstream of the pneumatic source (10). The venturi (40) is configured to receive a source flow (16) from the source (10) at a mass flow rate, the mass flow rate being between a lower, nominal flow rate value and a higher, graded flow rate value. The venturi (40) is sized such that when the mass flow rate is at the nominal flow rate value, a line pressure inside the line (30) corresponds to a source pressure upstream of the venturi (40), and when the mass flow rate to the venturi (40) is at the graded flow rate value, the line pressure is less than the source pressure.


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    Titel :

    AIRCRAFT PNEUMATIC SYSTEM


    Weitere Titelangaben:

    PNEUMATISCHES FLUGZEUGSYSTEM
    SYSTÈME PNEUMATIQUE D'AÉRONEF


    Beteiligte:
    OLVER BRYAN W (Autor:in) / ALECU DANIEL (Autor:in) / STINA NICK (Autor:in)

    Erscheinungsdatum :

    2021-08-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen



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