Fan blades with cyclic setting
AssigneeSnecma
InventorsPhilippe Pierre Vincent Bouiller, Stephane Rousselin
Life of this patent
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Abstract
A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360°/n, where n is an integer at least equal to 1.
Claims14
-13. (canceled)
A dual flow turbojet engine fan portion comprising:
- a plurality of fan blades;
- a disk to support the blades and configured to be rotated relative to a fan stator portion, along a longitudinal fan axis;
- a system for setting angles of attack associated with each fan blade, the systems configured so that an angle of attack of each blade varies according to a same setting law as a function of the angular position of the blade relative to the stator portion, along the longitudinal fan axis, the same setting law being periodic with period P=360°/n, with n corresponding to a whole number greater than or equal to 1.
Dependencies are inferred from the claim text.