Fan part for turbofan engine of aircraft, has strip whose geometry permits application of displacement parallel to axis, during its rotary movement with respect to stator part, to assure variation of blade incidence based on setting law

摘要

The fan part (1a) has a support disk (22) for supporting fan blades (20). An incidence setting system is associated to each blade and has a pin (36) that is firmly mounted on a root (30) of the corresponding blade in an off-centered manner. The system has a guiding strip (38) fixed with respect to a stator part (4). Geometry of the strip permits application of additional displacement parallel to a longitudinal axis (2) of the fan part, during its rotary movement with respect to the stator part along the axis, to assure variation of incidence of the blade based on a cyclic setting law. An independent claim is also included for a turbojet engine comprising an aerodynamic fairing.