A fan nozzle for an aircraft gas turbine engine is comprised of a core engine cowl that is disposed within a fan cowl so that an air flow area is defined therebetween. The core engine cowl and fan cowl are disposed around a horizontal central plane. The fan cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a first radius and a lower substantially semi-circular portion having a second radius. The core engine cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a third radius and a lower substantially semi-circular portion having a third radius. The upper substantially semi-circular portion of the core engine cowl includes a left arcuate member and a right arcuate member. The second radius is less than the first radius and the third radius is less than the fourth radius.


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    Title :

    ASYMMETRIC FAN NOZZLE IN HIGH-BPR SEPARATE-FLOW NACELLE


    Additional title:

    ASYMMETRISCHE FÄCHERDÜSE IN EINER GONDEL MIT HOHEM NEBENSTROMVERHÄLTNIS UND GETRENNTEM DURCHFLUSS
    TUYÈRE DE SOUFFLANTE ASYMÉTRIQUE DANS UNE NACELLE À ÉCOULEMENT SÉPARÉ À BPR ÉLEVÉ


    Contributors:

    Publication date :

    2018-04-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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