| 摘要 |
A composite turbomachine blade (34) comprises a composite material including reinforcing fibres in a matrix material, the turbomachine blade (34) comprises an aerofoil portion (36), a shank portion (38) and a root portion (40). The aerofoil portion (36) has a leading edge (42), a trailing edge (44). The composite turbomachine blade (34) also has a metallic protective member (52) arranged in the region of the leading edge (42) of the aerofoil portion (36) of the turbomachine blade (34). The metallic protective member (52) is adhesively bonded to the composite material in the region of the leading edge (42) of the aerofoil portion (36) of the composite turbomachine blade (34). The metallic protective member (52) has at least one metallic projection (56, 58) extending from the metallic protective member (52) towards the root portion (40) of the composite turbomachine blade (34). The at least one metallic projection (56, 58) reduces local peak stress levels and increases high cycle fatigue strength in the composite material, the adhesive and the metallic protective member. |
