A bleed air pressure regulation system for an aircraft anti-icing system comprises a first, upstream pressure regulating valve and a second, downstream pressure regulating valve arranged in series in a bleed airflow path. The respective pressure regulating valves each have a regulating pressure chamber in fluid communication with a respective pressure setting valve. Each pressure setting valve is in fluid communication with a bleed air inlet upstream of the first, upstream pressure regulating valve. The first, upstream pressure regulating valve is set to regulate the pressure of the bleed air to a first pressure and the second, downstream pressure regulating valve is set to regulate the pressure of the bleed air to a second pressure which is higher than the first pressure.


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    Title :

    Anti-icing systems


    Contributors:
    JONES TONY (author)

    Publication date :

    2018-08-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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 / F16K VALVES , Ventile



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