Patent ID: 8657576
Filing Date: 2014-02-25
Classification: F01D,F05D

Abstract:
1. An aerofoil for a gas turbine engine and for use with coolant, the aerofoil comprising: a divider wall; a chamber wall; a passage partly defined by the divider wall, along which the coolant flows; a chamber defined partly by the divider wall and the chamber wall; and a plurality of feed apertures defined by the divider wall to supply the coolant to impinge on the chamber wall, the feed apertures defining a center-line, an entry plane and an exit plane, at least one of the center-lines of the feed apertures including a continuously curved center-line extending, in a plane parallel to the coolant flow, between the entry plane and the exit plane, wherein the divider wall includes a thickened part through which the feed apertures are defined, the center-line at the entry plane is angled (θ) between 30 and 60 degrees from the coolant flow direction, and the center-line at the exit plane is angled (β) up to 30 degrees to the surface of the chamber wall.