Patent ID: 8215910

Claim:
An aircraft turbomachine fan comprising: a turbomachine inlet cone that has an exterior surface intended to be closely followed by a flow section of the turbomachine; a fan disk; fan blades which are mounted on said disk with which disk the blades rotate about an axis of rotation of the fan; an annular balancing flange that rotates as one with the fan disk about said axis of rotation and is equipped with a plurality of weight-fixing holes spaced circumferentially apart; one or more balancing weights mounted fixedly on said annular balancing flange by means of one or several of said weight-fixing holes, said annular balancing flange being positioned inside said inlet cone in such a way that weight-fixing holes of the annular balancing flange are isolated from said flow section of the turbomachine; and a fan blade retaining ring for axially retaining the blades with respect to said fan disk, said retaining ring and said annular balancing flange being produced as a single piece.