A gas turbine fan jet has a pair of contra rotating fans each of which is driven by an electrical induction motor 3, 5 and each is governed by a controller 2,7. A power generator 8 supplies electricity, which may be three phase, to the motors. The generator may be shaft driven by the turbine. Air is drawn in by the fans around and through the duct and flows over cooling vanes 10 in which are cooling channels Fig 2, 11. A moveable baffle or door 9 may regulate air flow over the vanes. The vanes may cool the compressor and turbine housing. The device seeks to increase fuel efficiency by replacing prior art mechanical gearboxes and drives to the fans by use of superconducting electrical motors and an adaptive learning intelligent control system.


    Access

    Download


    Export, share and cite



    Title :

    Dual servo differential turbofan engine


    Contributors:

    Publication date :

    2022-03-30


    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 / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



    Dual cycle turbofan engine

    SCHWEIGER, F. | AIAA | 1987


    Turbofan engine and aircraft comprising turbofan engine

    GARDES PASCAL / MENOU FABIEN / GOUGEON PASCAL et al. | European Patent Office | 2021

    Free access

    TURBOFAN ENGINE

    LIESER JAN / BOEHNING PEER | European Patent Office | 2019

    Free access

    Turbofan engine

    NICHOLAS GRECH / CHRISTOPHER A MOSLEY / JOHN R WELLS | European Patent Office | 2020

    Free access

    TURBOFAN ENGINE NOZZLE

    European Patent Office | 2017

    Free access