| 摘要 |
A blade for a gas turbine engine includes a root portion, an aerofoil portion and a transition portion between the root portion and the aerofoil portion. The aerofoil portion and the transition portion are defined by first and second wall members, the first and second wall members being secured together in the transition portion and each having an outer surface. The outer surface of at least one of the first and second wall members is generally concave in the transition portion in a radial direction of the blade.
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