A gas turbine engine assembly (16) includes a plurality of fan blades (20) rotatable about a fan rotation axis (A); a fan nacelle (26) at least partially surrounding the plurality of fan blades (20), the fan nacelle (26) defining an inlet (54); at least one sensor (42,40) positioned forward of the fan nacelle (26), the at least one sensor (42,40) generating a signal indicative of an airflow condition entering the inlet (54); an effector (14) that is actuatable to accommodate distortions in inlet airflow; and a controller (48) receiving the signal from the at least one sensor (42,40) and determining an inlet distortion condition corresponding to the signal indicative of an airflow condition and actuating the effector (14) based on the identified inlet distortion condition.


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    Title :

    PREDICTION OF INLET DISTORTION OF BOUNDARY LAYER INGESTING PROPULSION SYSTEM


    Additional title:

    VORHERSAGE VON EINLASSVERZERRUNG EINES GRENZSCHICHTAUFNAHMEANTRIEBSSYSTEMS
    PRÉDICTION DE LA DISTORSION D'ENTRÉE DE SYSTÈME DE PROPULSION D'INGESTION DE COUCHE LIMITE


    Contributors:

    Publication date :

    2022-03-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT