| 摘要 |
A vane for a gas turbine engine includes an aerofoil part and a shroud that forms a sealing part at one end of the aerofoil part. The sealing part defines a cavity and an opening to the cavity. The sealing part may include a pair of opposed side walls extending from a radially outer wall of the shroud to a pair of radially inner walls of the shroud to define a cavity. The pair of radially inner walls may be substantially parallel to the radially outer wall and may extend in a substantially circumferential direction to define a cavity opening.
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