A flow control system on an aircraft engine nacelle (14) incorporates a plurality of translating turning vanes (17a-17e) each having a body. An equal plurality of actuators (30) is coupled to a trailing edge of the body of an associated one of the translating turning vanes (17a-17e). The actuator (30) translates the body from a retracted position to an extended position.


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    Title :

    TRANSLATING TURNING VANES FOR A NACELLE INLET


    Additional title:

    TRANSLATORISCHE UMLENKBLECHE FÜR EINEN GONDELEINLASS
    TRANSLATION D'AUBES DIRECTRICES POUR UNE ENTRÉE DE NACELLE



    Publication date :

    2019-01-02


    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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