A gas turbine engine nacelle (40) comprising an intake liner (150). The liner (150) comprises a plurality of cells (52). Each cell (52) comprises an open radially inner end (54) in fluid communication with an interior side (42) of the nacelle (40), and an open radially outer end (56) in fluid communication with an exterior side (44) of the nacelle (40). Each open end (54, 56) of each cell (52) defines a respective cross sectional area. The intake liner (150) further comprises radially inner and outer facing sheets (58, 44) overlying a respective radially inner and outer open ends (54, 56) of the respective cell (52). Each facing sheet (58, 44) defines at least one aperture (60, 61) overlying at least one cell (52), an overlying portion of the respective aperture (60, 61) having a smaller cross sectional area than the respective open end of the respective cell.


    Access

    Download


    Export, share and cite



    Title :

    AIRCRAFT ENGINE NACELLE


    Additional title:

    FLUGZEUGMOTORGONDEL
    NACELLE POUR MOTEUR D'AVION


    Contributors:

    Publication date :

    2019-01-09


    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



    AIRCRAFT ENGINE NACELLE

    WILLIAMS GEOFFREY / SALISBURY ROSS / PEACOCK ANTONY | European Patent Office | 2020

    Free access

    Aircraft engine nacelle

    NAMGOONG HOWOONG | European Patent Office | 2018

    Free access

    AIRCRAFT ENGINE NACELLE

    WILLIAMS GEOFFREY RICHARD / SALISBURY ROSS / PEACOCK ANTONY | European Patent Office | 2021

    Free access

    AIRCRAFT ENGINE NACELLE

    NAMGOONG HOWOONG | European Patent Office | 2017

    Free access

    Aircraft engine nacelle

    GRALL LOÏC / SERISET MÉLODY / HEAU ALEXIS et al. | European Patent Office | 2022

    Free access