| 摘要 |
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.
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