A fan assembly (16) for gas turbine engine (18) includes a plurality of fan blades (20) rotatable about a fan rotation axis (A), each of the plurality of fan blades movable about an axis (46) transverse to the fan rotation axis (A), a fan nacelle (26) partially surrounding the plurality of fan blades (20), and a pitch mechanism (40) coupled to the plurality of blades (20) that changes an angle of pitch for each of the plurality of blades corresponding to a circumferential position of the fan blade about the fan rotation axis (A).
BOUNDARY LAYER INGESTING FAN
GRENZSCHICHTFAN
SOUFFLANTE D'INGESTION DE COUCHE LIMITE
2025-04-09
Patent
Electronic Resource
English
Boundary-Layer-Ingesting Inlet Flow Control
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