| 摘要 |
An aerofoil 20 for a gas turbine engine comprises a wall or walls 22 defining an interior 24 along which cooling air may flow in a first direction C, at least one wall 22 defining a passage 26 extending from an interior surface to an exterior surface of the wall 22 through which the cooling air may flow in a second direction D. The passage 26 has an inlet area defined by the interior surface of the wall 22, the inlet area having a shape which is elongated along an axis which is substantially parallel with the first direction C of the cooling air. External fluid may flow across the aerofoil in a third direction, and the cooling air may exit the passage 26 in the third direction. An outlet area 34 of the passage 26 may be elongated along an axis which is substantially parallel with the third direction. The passage inlet and outlet 34 may be substantially oval or elliptical. A plurality of regularly spaced passages 26 may be provided in a turbine blade or nozzle guide vane.
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