| 摘要 |
A core 14 for use in a casting a blade or vane of a gas turbine engine (Figure 1) comprises a first portion 20 and a second thinner-walled portion 22 extending from the first portion 20 towards a terminal edge. The second portion 22 has beads 38 which define its opposite lateral edges 26 in order to reduce cracking or other damage thereto. This portion also has a rib 24 at its terminal edge which forms a through slot at the trailing edge of the cast blade or vane and holes 28 which form pedestals within the cast blade or vane. A cast component made using the core has an aerofoil portion 2 and shroud portions 6, with the hollow regions 42 formed by the beads 38 situated at the transitions from the aerofoil portion 2 to the shroud portions 6.
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