A nacelle assembly (16) for a gas turbine engine includes a fan nacelle (62) bounding a bypass flow path (B). The fan nacelle (62) includes a first nacelle section (68A) and a second nacelle section (68B). The second nacelle section (68B) includes a moveable portion (79) movable relative to a forward portion (81) to define a secondary flow passage (74). The first nacelle section (68A) includes an inlet lip (71). A thrust reverser (72) is configured to selectively communicate a portion of bypass airflow between the bypass flow path (B) and the secondary flow passage (74). A pump (88) is configured to selectively communicate airflow between the inlet lip (71) and the secondary flow passage (74).


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    Title :

    COMBINED INLET LAMINAR AND THRUST REVERSER CASCADE EFFLUX FLOW CONTROL SYSTEM


    Additional title:

    KOMBINIERTES REGELSYSTEM DER STRÖMUNG EINES LAMINAREN EINLAUFS UND EINES KASKADENSCHUBUMKEHRERS
    SYSTÈME DE COMMANDE D'ÉCOULEMENT D'EFFLUENT EN CASCADE LAMINAIRE D'ENTRÉE COMBINÉE ET D'INVERSEUR DE POUSSÉE


    Contributors:

    Publication date :

    2020-03-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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