A method of controlling an aircraft bleed may include the steps of monitoring (302) a temperature of a precooled airflow (140) exiting a precooler (106), and determining (304) a status of a wing anti-ice system (102) of an aircraft. The wing anti-ice system (102) may be configured to receive the precooled airflow (140) from the precooler (106). The method may further comprise the steps of determining (306) whether an engine operating condition of the aircraft is within an icing envelope (200), selecting (308) a temperature set point for the precooled airflow based on the status of the wing anti-ice system (102) and whether the aircraft is within an icing envelope (200), and modulating (310) a fan airflow from a fan (42) to the precooler (106) to adjust the temperature of the precooled airflow to the temperature set point.


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    Title :

    AIRCRAFT BLEED SYSTEM


    Additional title:

    FLUGZEUGZAPFSYSTEM
    SYSTÈME DE PURGE D'AÉRONEF


    Contributors:

    Publication date :

    2019-06-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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