Abstract: A disk/blade assembly for an aircraft engine compressor is disclosed. The assembly includes a disk and a plurality of blades with hammer attachment. Each blade includes a blade root provided with an upstream bearing surface situated on a leading edge side of the airfoil and a downstream bearing surface situated on a trailing edge side of this airfoil. The disk is provided with a circumferential groove in which the blade root of each of the blades is held by the bearing surfaces. For each of the blades, the downstream bearing surface is offset circumferentially from the upstream bearing surface in a given direction of offset, corresponding to the direction of offset between the trailing edge and the leading edge of the airfoil.

Abstract: The invention relates to a disk/blade assembly for an aircraft engine compressor, comprising a disk (2) and a plurality of blades with hammer attachment (6), each blade comprising a blade root provided with an upstream bearing surface (32) situated on a leading edge side of the airfoil and a downstream bearing surface (34) situated on a trailing edge side of this airfoil, the disk being provided with a circumferential groove (10) in which the blade root of each of the blades is held by means of the bearing surfaces. According to the invention, for each of the blades, the downstream bearing surface (34) is offset circumferentially from the upstream bearing surface (32) in a given direction of offset (42), corresponding to the direction of offset between the trailing edge (22) and the leading edge (20) of the airfoil.