| 摘要 |
An aerofoil blade or vane for a gas turbine engine comprises an aerofoil which includes one only of the two flanks of the trailing edge of the aerofoil and which is an integrally cast structure. The other flank of the trailing edge is formed as a separate piece which is metallurgically bonded to the remainder of the aerofoil through a joint face. The aerofoil is adapted for the supply of cooling fluid to its interior and the joint face is cut away to form an exit passage or passages for cooling fluid which leaves the interior of the aerofoil.
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