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Fan part for turbofan engine of aircraft, has incidence setting system configured such that incidence of blade varies, according to cyclic setting law, based on angular position of blade along axis, where law is periodic of specific period
Fan part for turbofan engine of aircraft, has incidence setting system configured such that incidence of blade varies, according to cyclic setting law, based on angular position of blade along axis, where law is periodic of specific period
The fan part (1a) has a support disk (22) for supporting fan blades (20) and rotated with respect to a stator part (4), along a longitudinal axis (2) of the fan part. Incident setting systems are associated with the corresponding blades. Each setting system is configured such that incidence of each blade varies, according to a cyclic setting law, based on an angular position of the blade with respect to the stator part along the axis. The setting law is periodic of a period P that is equal to division of 360 degree and n, where n corresponds to an integer greater or equal to one. An independent claim is also included for a turbojet engine comprising an aerodynamic fairing.
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