A propulsion system for an aircraft has at least two fans (22, 24; 122, 124; 208, 210), each fan (22...210) having a fan drive shaft (56; 156). A turboshaft gas turbine engine (26, 28; 126, 128; 202, 204) drives each of the at least two fans (22...210), and drive an output shaft (36; 136) which drives a gear (38; 138) to, in turn, engage for driving a gear (40; 140) on a first intermediate shaft (41, 42; 141; 206, 207) extending from the turboshaft gas turbine engine (26...204) in a rearward direction toward an intermediate fan drive shaft (50; 150). The intermediate fan drive shaft (50; 150) drives the fan drive shaft (56; 156), and the first intermediate shafts (41...207) extend over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine (26...204) and the fan (22...210) than in a width dimension defined between the at least two fans (22...210). The first intermediate shafts (41...207) are concentric.


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    Titel :

    CONCENTRIC SHAFTS DRIVING ADJACENT FANS FOR AIRCRAFT PROPULSION


    Weitere Titelangaben:

    BENACHBARTE VENTILATOREN ANTREIBENDE KONZENTRISCHE WELLEN FÜR FLUGZEUGANTRIEB
    ARBRES CONCENTRIQUES ENTRAÎNANT DES SOUFFLANTES ADJACENTES POUR LA PROPULSION DUN AÉRONEF


    Beteiligte:

    Erscheinungsdatum :

    2018-06-13


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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