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.
AIRCRAFT BLEED SYSTEM
FLUGZEUGZAPFSYSTEM
SYSTÈME DE PURGE D'AÉRONEF
2019-06-19
Patent
Elektronische Ressource
Englisch
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