A propulsion system (20) is provided for an aircraft. This aircraft propulsion system (20) includes a gas turbine engine core (26), a first propulsor rotor (22) and a second propulsor rotor (24). The gas turbine engine core (26) includes a compressor section (46), a combustor section (47), a turbine section (48) and a rotating structure (68). The rotating structure (68) includes a turbine rotor (60) within the turbine section (48). The first propulsor rotor (22) is rotatably driven by the rotating structure (68) during a first mode and a second mode. The first propulsor rotor (22) includes a plurality of variable pitch blades (30). The variable pitch blades (30) include a first blade (30) configured to pivot between a thrust position and an idle position. The first blade (30) is in the thrust position during the first mode. The first blade (30) is in the idle position during the second mode. The second propulsor rotor (24) is rotatably driven by the rotating structure (68) during the second mode.


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    Title :

    AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR


    Additional title:

    FLUGZEUGANTRIEBSSYSTEM MIT EINSTELLBAREM SCHUBANTRIEB
    SYSTÈME DE PROPULSION D'AÉRONEF AVEC PROPULSEUR DE POUSSÉE RÉGLABLE


    Contributors:

    Publication date :

    2023-11-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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