Method for balancing a set of blades

System for balancing a set of blades (5) that will be arranged on a bare disk (7) of an aircraft engine, the bare disk (7) comprising a determined number of numbered slots (a) that will hold the same determined number of blades that can have a dispersion of mass, said system being characterised in that it comprises a processor configured to:

• sort the blades (5) by monotonic order of their mass (mi), forming an ordered set of blades,
• separate the ordered set of blades in a balanced manner into four lobes composed of a first large lobe (GL1), a second large lobe (GL2), a first small lobe (PL1) and a second small lobe (PL2), the blades being sorted in each lobe in a current placement order,
• arrange the four lobes (GL1, GL2, PL1, PL2) on the bare disk (7) such that the current placement order of the blades corresponds to the numbered slots of the bare disk, and
• arrange the four lobes (GL1, GL2, PL1, PL2) on the bare disk (7) in a configuration determined as a function of a first out-of-balance vector (B1) representative of an out-of-balance inherent to the bare disk, and
• reorganise the blades in the different lobes using an iterative permutation process adapted to balance the first out-of-balance vector by a second out-of-balance vector resulting from the mass dispersion of the blades and their arrangements on the disk, said reorganisation defining a final placement order of the blades on the disk slots.