Film-cooled component, eg gas turbine engine blade or vane

摘要

A component 56 such as a blade or vane of a gas turbine engine is provided which has a surface 62 to be film cooled and at least one passage 58 for coolant fluid which extends within the component 56 and emerges at the surface 62, characterised in that an expansion recess 60 is disposed in the surface 62 in communication with the passage 58, the base 66 of the recess 60, at its junction with the passage 58, being inclined by not less than 10{ to the axis of the passage 58 at the junction. The base 66 of the recess 60 may be parallel or inclined with respect to the surface 62. The recess 60 may extend partially around the periphery of the passage 58 on the downstream side.