A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct. The gas turbine engine further comprises an inner cowl which provides an aerodynamic fairing surrounding the engine core, the inner cowl being rearwards of the inner ring, and including two door sections located on respective and opposite sides of the engine, each door section being pivotably openable about an upper edge thereof to enable maintenance access to the engine core. The gas turbine engine further comprises a keel beam which extends rearwardly from the inner ring at bottom dead centre thereof to provide latching formations for latching to a lower edge of each door section when it is closed.


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    Title :

    GAS TURBINE ENGINE KEEL BEAM


    Additional title:

    GASTURBINENMOTORKIELSTRAHL
    POUTRE DE QUILLE DE MOTEUR À TURBINE À GAZ


    Contributors:

    Publication date :

    2019-10-30


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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