An anti-icing system for an aircraft nacelle structure is provided that includes a controllable PRSOV, a circumferentially extending duct, a bleed air duct segment, at least one PRV, and a controller. The PRSOV may be disposed in a closed or an open configuration. The PRV is disposed downstream of the PRSOV and in fluid communication with the bleed air duct segment. The PRV may be disposed in a closed or in an open configuration. The controller is in communication with a memory storing instructions. The instructions when executed cause the system controller to control the PRSOV to maintain bleed air within the anti-icing system within a predetermined range of operating pressures by selectively controlling the PRSOV into at least one of the one or more PRV open configurations, and control the PRV to open to maintain the bleed air below the maximum pressure.


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    Title :

    AIRCRAFT ANTI-ICING SYSTEM


    Contributors:

    Publication date :

    2024-08-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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