BLADE FOR A GAS TURBINE

摘要

A blade (20) for a gas turbine, in particular for the low-pressure turbine of a gas turbine with sequential combustion, is produced by a casting process and has an aerofoil which extends in a radial direction between an inner platform and an outer platform (21) and in the interior of which there is a cooling duct, which runs past the platforms (21) and through which there flows a cooling medium, in particular cooling air, for cooling the blade (20), wherein the outer and/or inner platform (21) has core outlets (40), which originate from the use of a casting core, connect the cooling duct to the space outside and are closed by a closure element (32).  In the case of such a blade (20), optimum cooling is ensured by the closure elements (32) being formed and fitted into the core outlets (40) in such a way that they finish flush with the wall surface of the cooling duct.