| 摘要 |
#CMT# #/CMT# 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. #CMT# : #/CMT# An independent claim is also included for a turbojet engine comprising an aerodynamic fairing. #CMT#USE : #/CMT# Fan part for a turbojet engine (claimed) i.e. turbofan engine, that is partially buried in a main wing of an aircraft. #CMT#ADVANTAGE : #/CMT# The fan part is configured such that incident setting systems share a singe toothed wheel, thus reducing the mass and encumbrance of the fan part. The single cyclic setting law permits reducing of the incidence of the blade when the blade enters in a buried zone in case of partially buried turbojet engine, such that the blade requires less air, thus reducing the pumping risk and improving the efficiency of the engine. The fan part is configured such that the cyclic setting law responds to permanent or occasional heterogeneous supply of air to the fan, in a satisfactory manner. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a front view of a turbojet engine. 1a : Fan part 2 : Longitudinal axis 4 : Stator part 20 : Fan blades 22 : Support disk. |
