A gas turbine engine (10) has a core engine (10) with an engine axis, a fan bypass duct (22) terminating in a bypass exhaust nozzle (23), and a pylon fairing (24) extending across the bypass duct (22) at a given angular position enclosing a pylon (101). The pylon fairing (24) has a leading edge inside the duct (100, 22) upstream of the bypass exhaust nozzle (23) and a trailing edge downstream of the bypass exhaust nozzle (23). The bypass duct (22) is notionally divided into first and second halves to either side of a plane at 90° to the given angular position and containing the engine axis. The first half is opposite to the pylon fairing (24). At the exhaust nozzle (102, 23) the flow area of the second half (22A, 22B) is substantially equal to that of the first half (22A, 22B)


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    Title :

    DUCTED FAN GAS TURBINE ENGINE


    Additional title:

    BYPASS-GASTURBINENMOTOR
    MOTEUR DE TURBINE À GAZ À DOUBLE FLUX


    Contributors:

    Publication date :

    2019-02-06


    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



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