A bleed air pressure regulation system (30) for an aircraft anti-icing system comprises a first, upstream pressure regulating valve (32) and a second, downstream pressure regulating valve (34) arranged in series in a bleed airflow path (28). The respective pressure regulating valves (32, 34) each have a regulating pressure chamber (74) in fluid communication with a respective pressure setting valve (82, 84). Each pressure setting valve (82, 84) is in fluid communication with a bleed air inlet (88, 96) upstream of the first, upstream pressure regulating valve (32). The first, upstream pressure regulating valve (32) is set to regulate the pressure of the bleed air to a first pressure and the second, downstream pressure regulating valve (34) 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


    Additional title:

    Antifrostsysteme
    Systèmes antigivrage


    Contributors:
    JONES TONY (author)

    Publication date :

    2018-10-03


    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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