Patent ID: 7959410

Claim:
A disk/blade assembly for an aircraft engine compressor comprising: a disk; and a plurality of blades with hammer attachment mounted on said disk, each blade comprising successively, in an inward radial direction, an airfoil including a leading edge and a trailing edge offset circumferentially from said leading edge in a given direction of offset, a platform, a stilt, and 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, wherein the disk is provided with a circumferential groove in which said blade root of each of said plurality of blades is held by said bearing surfaces resting against the circumferential groove, wherein, for each blade of said plurality of blades, the downstream bearing surface is offset circumferentially from the upstream bearing surface in said given direction of offset, wherein, for each blade of said plurality of blades, the blade root includes two opposite circumferential end surfaces arranged on either side of said bearing surfaces, the circumferential end surfaces each includes a substantially concave shape.