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


    Access

    Download


    Export, share and cite



    Title :

    TRANSLATING TURNING VANES FOR A NACELLE INET



    Publication date :

    2018-12-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    TRANSLATING TURNING VANES FOR A NACELLE INLET

    HOISINGTON ZACHARY C / PALACIOS FRANCISCO D / HOFFMAN DREW C et al. | European Patent Office | 2025

    Free access

    Translating turning vanes for a nacelle inlet

    HOISINGTON ZACHARY C / PALACIOS FRANCISCO D / HOFFMAN' DREW C et al. | European Patent Office | 2019

    Free access

    AIR INTAKE OF A TURBOJET ENGINE NACELLE COMPRISING GUIDE VANES

    BINDER ANTHONY / MINCU DANIEL-CIPRIAN | European Patent Office | 2022

    Free access

    Air intake of a turbojet engine nacelle comprising guide vanes

    BINDER ANTHONY / MINCU DANIEL-CIPRIAN | European Patent Office | 2023

    Free access

    LOCKABLE TRACK SYSTEM FOR A TRANSLATING NACELLE STRUCTURE

    LU JINQIU | European Patent Office | 2020

    Free access