The present application provides a gas turbine engine (10) for an aircraft and an aircraft, the gas turbine engine being arranged below a wing (52) of the aircraft and comprising an engine core (11) comprising a turbine (19), a compressor (14) and a mandrel (26) connecting the turbine to the compressor, said turbine (19) comprising a lowest pressure rotor stage (19b) and having a turbine diameter(122); a fan (23) located upstream of the engine core (11), the fan comprising a plurality of fan blades (64) extending from a hub (66); and a gearbox (30) that receives input from the mandrel (26) and outputs a drive to the fan (23) so as to drive the fan at a lower rotational speed than the mandrel. The downstream blocking ratio is in the range of 0.2 to 0.3.


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    Titel :

    Turbine engine


    Erscheinungsdatum :

    2019-02-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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