Cooled aerofoil for a gas turbine engine

摘要

A cooled aerofoil, such as the aerofoil of a nozzle guide vane, for a gas turbine engine has a cooling system in which the release of cooling fluid on the convex suction flank is avoided. The cooling system utilises a thin skin 28 which overlays the contoured surface 27 of the convex flank to form a plurality of passageways. A first flow of cooling fluid enters these passages via a plurality of impingement holes 30 and leaves via cross flow passages 31 and 32. The cross flow passages allow the fluid to pass to the opposed, pressure flank of the aerofoil where it leaves the aerofoil via film cooling holes 37.