A bleed air system for a pneumatic system of an aircraft includes a low-pressure bleed tap configured to bleed a low-pressure compressed air from a low-pressure source; a high-pressure bleed tap configured to bleed a high-pressure compressed air from a high-pressure source; an upstream duct configured to receive one or both of the low-pressure compressed air and the high-pressure compressed air; a downstream duct configured to provide a regulated compressed air to the pneumatic system; a high-pressure shutoff valve positioned between the high-pressure bleed tap and the upstream duct; a low-pressure non-return valve positioned between the low-pressure bleed tap and the upstream duct; a pressure regulating and shutoff valve positioned between the upstream duct and the downstream duct, the pressure regulating and shutoff valve configured to generate the regulated compressed air; and a pressure relief valve positioned within the upstream duct.


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    Titel :

    Dual-pressure source aircraft pneumatic system with pressure relief


    Beteiligte:
    ANDELSON PHILLIP (Autor:in) / PORTH EDWARD J (Autor:in) / SUARES ALEX (Autor:in) / EISHEN JEFFREY (Autor:in)

    Erscheinungsdatum :

    2022-09-20


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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