An apparatus (100) is provided including an auxiliary power unit (114) positioned within an aircraft. A reverse thrust assembly (126) is driven by the auxiliary power unit (114) to provide reverse thrust during landing of the aircraft. An air flow surface (130) having a first boundary layer (134, 158) of moving fluid when external air (132) is flowed along the airflow surface (130) which could be a nacelle (112), pylon (110) or any other aircraft surface. A movable member (144, 152) is configured to move between a first position (146, 148) to direct the boundary layer (134, 158) to the auxiliary power unit (114) during climb and cruise of the aircraft, and to a second position (146, 148) to direct a freestream air feed (142) to the auxiliary power unit (114) during landing of the aircraft. Further, the movable member (144, 152) may switch to a third conduit (138, 140, 154) to extract the boundary layer (134, 158) from the interior surface of an engine air intake (156) to reduce the main engine inlet losses and distortion.


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    Title :

    AIRCRAFT BOUNDARY LAYER REMOVAL WITH AUXILLIARY POWER UNIT SUCTION


    Additional title:

    FLUGZEUGGRENZSCHICHTENTFERNUNG MIT HILFSTRIEBWERKSANSAUGEN
    ÉLIMINATION DE LA COUCHE LIMITE D'AÉRONEF AVEC ASPIRATION UNITÉ D'ALIMENTATION AUXILIAIRE


    Contributors:

    Publication date :

    2018-06-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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