A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter along the radial direction. The core engine defines an overall core axial length along the axial direction and an under-core cowl axial length along the axial direction. The gas turbine engine defines a core cowl diameter ratio equal to the peak cowl diameter divided by the maximum combustor casing diameter and a core cowl length ratio equal to the under-core cowl axial length divided by the overall core axial length.


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    Titel :

    GAS TURBINE ENGINE


    Beteiligte:

    Erscheinungsdatum :

    19.06.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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