| 摘要 |
A fan or compressor blisk for a gas turbine engine, lift fan or the like, comprises a disc having a radially outer rim 42, and a plurality of aerofoil blades 22 circumferentially spaced around and extending radially outwards from the rim. The rim has a radially inward facing surface 50 on its underside on at least one side of the disc, the radially inward facing surface having at least one indentation 54 for reducing the cross-sectional area of the rim, in the circumferential direction of the disc, in the region of the indentation.
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