| 摘要 |
PROBLEM TO BE SOLVED: To provide a disk/blade assembly having a hammer installing part for removing the problem on an embodiment of a conventional technology. SOLUTION: This invention relates to the disk/blade assembly for the aircraft engine compressor including a disk 2 and a plurality of blades 6 having the hammer installing part. The respective blades include a blade root part provided with an upstream bearing surface 32 positioned on the front edge side of aerofoil and a downstream bearing surface 34 positioned on the rear edge side of this aerofoil. The disk is provided with a peripheral edge groove 10 for holding the blade root part of the respective blades by the bearing surface. In the plurality of respective blades in this invention, the downstream bearing surface 34 deflects in a peripheral edge shape in the given deflection 42 direction coincident with the deflection direction between the rear edge 22 and the front edge 20 of the aerofoil from the upstream bearing surface 32. COPYRIGHT: (C)2008,JPO&INPIT |
