| 摘要 |
A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) which has an inner surface (62), an outer surface (64), an upstream flange (42) and a downstream flange (52). The outer surface (64) of the metal casing (40) is provided with a pattern of blind apertures (66) which extend radially inwardly from the outer surface (64) of the metal casing (40) between the flanges (42,52). The fan blade containment has reduced weight of the metal casing (40) of the fan blade containment assembly (38) for a large diameter turbofan gas turbine engine but has unimpaired stiffness and penetration resistance. The apertures may alternatively be formed in the inner surface and various configurations of apertures are disclosed. An acoustic honeycomb lining (74) and reinforcing fibres (70) may also be provided.
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