A gas turbine engine includes a gas generator that has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of the at least one gas generator turbine rotor. The fan drive turbine drives a driveshaft and the driveshaft engages gears to drive at least three fan rotors. The driveshaft extends away from the gas generator such that at least one of the fan rotors that is positioned remotely from the fan drive turbine on the driveshaft is spaced to be either more forward or more rearward of the fan drive turbine relative to at least one of the fan rotors positioned closer to the fan drive turbine. An aircraft is also disclosed.


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    Titel :

    GAS TURBINE ENGINE WITH DISTRIBUTED FANS DRIVEN ON ANGLED DRIVE SHAFT


    Beteiligte:

    Erscheinungsdatum :

    17.12.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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