METHOD FOR ALTERING THE LAW OF TWIST OF THE AERODYNAMIC SURFACE OF A GAS TURBINE ENGINE FAN BLADE

摘要

The invention relates to a method for altering the law of twist of the aerodynamic surface of a gas turbine engine fan blade, in which method there is established, for a portion of the aerodynamic surface of the fan blade, an alteration law defined by a variation in a pitch angle of the blade as a function of a radial height thereof, said alteration law comprising alterations each defined by a height on the radial height of the fan blade and by an amplitude, and the alteration law thus established is applied to a law governing the initial twist (C) of the fan blade in order to obtain an altered twist law (Calt; C'alt) for the fan blade, said initial twist law being defined by a polynomial of the radial height of the fan blade as a function of its pitch angle.