A nacelle defining an intake is provided for channelling and conditioning freestream airflow to a fan of a ducted fan gas turbine engine. The nacelle intake comprises in flow series an intake lip, and a diffuser. The intake lip has at its forwardmost end a highlight which is a closed loop defining a boundary between inner and outer surfaces of the nacelle, and the diffuser terminates at its rearwardmost end at a front face of the fan. The intake has a circumferentially extending shock control bump or a series of circumferentially spaced shock control bumps formed thereon. On longitudinal cross sections through the intake containing the bump or series of bumps: the bump or each bump of the series of bumps has a profile which forms in flow series an up-ramp, a maximum and a down-ramp, at least one of the up-ramp and the down-ramp forming an inflection point or curvature discontinuity point on the profile, and the inflection point or curvature discontinuity point being axially located between the highlight and a position which is axially rearward therefrom by a distance of no more than 0.6 L, where L is the axial distance between the highlight and the front fan face.


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    Title :

    NACELLE INTAKE


    Contributors:

    Publication date :

    2020-04-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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