The invention relates to an aircraft comprising a fuselage (1), which is propelled by a turbine engine with two coaxial fans, namely an upstream fan (7) and a downstream fan (8), driven by two contra-rotating rotors (5, 6) of a power turbine (3). The two fans (7, 8) and the turbine (3) are integrated into a nacelle (14) which projects downstream from the fuselage (1) and through which air flows. According to the invention, at least one of the fans (7, 8) of the aircraft and, in particular, the downstream fan (8) comprises variable-spacing blades, and at least one stator-forming variable-spacing blade ring (25) in the aircraft is placed upstream of the upstream fan (7). The variable-spacing stator blades (25) and the variable-spacing blades of the downstream fan (8) are mutually configured to direct the air flow in a first mode in which the air flows through the nacelle (14) from upstream to downstream and in a second mode in which the air is pushed back upstream through the nacelle (14).


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    Title :

    AERONEF COMPORTANT DEUX SOUFFLANTES CONTRAROTATIVES A L'ARRIERE D'UN FUSELAGE AVEC CALAGE DES AUBES DE LA SOUFFLANTE AVAL


    Additional title:

    AIRCRAFT COMPRISING TWO CONTRA-ROTATING FANS TO THE REAR OF THE FUSELAGE, WITH SPACING OF THE BLADES OF THE DOWNSTREAM FAN
    LUFTFAHRZEUG MIT ZWEI GEGENLÄUFIGEN BLÄSERN AM HECK DES RUMPFES UND MIT VERSTELLBAREN SCHAUFELBLÄTTERN DES NACHGELAGERTEN BLÄSERS


    Contributors:

    Publication date :

    2019-08-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    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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