Fan blades with cyclic setting

Details Fan blades with cyclic setting Fan blades with cyclic setting

F - Mech Eng,Light,Heat,Weapons

04

D

F04D 29/32 (2006.01) F02K 3/06 (2006.01) F04D 29/36 (2006.01)

Patent

CA 2751805

The present invention relates to a fan portion (1a) of a dual flow turbojet engine including a plurality of fan blades (20), a disk (22) for supporting the blades and capable of being rotated relative to a stator portion (4) of the fan, along a longitudinal axis (2) of the fan, as well as to a system for setting the angle of attack associated with each fan blade, said systems being designed 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 (2), said same setting law being periodic with a period of P = 360°/n, where n is an integer at least equal to 1.

La présente invention se rapporte à une partie soufflante (1a) de turboréacteur à double flux comprenant une pluralité d'aubes de soufflante (20), un disque (22) de support des aubes capable d'être mis en rotation par rapport à une partie stator (4) de soufflante, selon un axe longitudinal (2) de soufflante, ainsi qu'un système de calage en incidence associé à chaque aube de soufflante, ces systèmes étant conçus de telle sorte que l'incidence de chaque aube varie selon une même loi de calage fonction de la position angulaire de l'aube par rapport à la partie stator, selon l'axe longitudinal (2), cette même loi de calage étant périodique de période P = 360°/n, avec n correspondant à un nombre entier supérieur ou égal à 1.

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