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.
AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR
FLUGZEUGANTRIEBSSYSTEM MIT EINSTELLBAREM SCHUBANTRIEB
SYSTÈME DE PROPULSION D'AÉRONEF AVEC PROPULSEUR DE POUSSÉE RÉGLABLE
2023-11-29
Patent
Elektronische Ressource
Englisch
AIRCRAFT PROPULSION SYSTEM WITH ADJUSTABLE THRUST PROPULSOR
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