Abstract: In a process for producing a turbine blade or vane, providing a casting mold for casting the turbine blade or vane, the casting mold including a blade or vane platform and a main blade or vane part, and a position of the main blade or vane part relative to the blade or vane platform determining a first angle of incidence; providing additional machining stock to the blade or vane platform at predetermined locations; machining the casting using a process which is specified for the first angle of incidence; rotating the casting around a longitudinal axis for an angle which is equal to the difference between said first angle of incidence and a second angle of incidence, and subjecting said rotated casting to said machining process to remove at least partially the additional machining stock.

Abstract: A cooling arrangement (17) for supplying a first cavity (9) with a cooling gas, in particular in a gas turbine of a power plant, includes a cooling-gas passage (19) which is formed in a first component (6) and connects the first cavity (9) to a second cavity (10 ). A second component (16 ) bears against a bearing side (15) remote from the second cavity (10 ) and separates the first cavity (9) from a third cavity (12). The second component (16 ) is displaceable within a range of displacement. To improve the cooling effect, an orifice region (20) of the cooling-gas passage (19) is dimensioned and/or positioned in such a way that its orifice cross section (21) projects from the range of displacement to such an extent that it is open at least with a predetermined minimum cross section in any position of the second component (16 ).

Abstract: The present invention relates to a cooling arrangement (17) for supplying a first cavity (9) with a cooling gas, in particular in a gas turbine of a power plant, comprising a cooling-gas passage (19) which is formed in a first component (6) and connects the first cavity (9) to a second cavity (10). A second component (16) bears against a bearing side (15) remote from the second cavity (10) and separates the first cavity (9) from a third cavity (12). The second component (16) is displaceable within a range of displacement. To improve the cooling effect, an orifice region (20) of the cooling-gas passage (19) is dimensioned and/or positioned in such a way that its orifice cross section (21) projects from the range of displacement to such an extent that it is open at least with a predetermined minimum cross section in any position of the second component (16).

Abstract: In a process for producing a turbine blade or vane, a casting (10′) which is in the basic shape of the turbine blade or vane is produced in a casting mold, and the casting (10′) is then subjected to material-removing machining in order to complete the turbine blade or vane.