A gas turbine engine including: an engine core including a turbine, a compressor, and a core shaft; a fan located upstream of the engine core; a gearbox; and a fan shaft mounting structure including at least two supporting bearings connected to fan shaft. The supporting bearings are located at positions forward of the gearbox. A first bearing separation distance (d1) is defined as an axial distance between the input to the fan and the closest supporting bearing in a rearward direction from the fan. A bearing axial separation (d3) is defined as an axial distance between the closest supporting bearing in the rearward direction from the fan and the closest supporting bearing in a forward direction from the gearbox. A bearing separation ratio defined as:the⁢first⁢bearing⁢separation⁢distance⁢(d1)the⁢bearing⁢axial⁢separation⁢(d3)is in a range from 4.1×10−1 to 8.3×10−1.


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    Titel :

    AIRCRAFT ENGINE


    Beteiligte:
    SPRUCE MARK (Autor:in)

    Erscheinungsdatum :

    22.09.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F16H Getriebe , GEARING / F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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