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A method for producing a coated turbine blade, with which the frequency property thereof can be particularly easily adjusted to the required boundary conditions is provided. Recesses are introduced into a blade tip of the blade leaf of the turbine blade after coating of turbine blade. In one aspect

A method for producing a coated turbine blade, with which the frequency property thereof can be particularly easily adjusted to the required boundary conditions is provided. Recesses are introduced into a blade tip of the blade leaf of the turbine blade after coating of turbine blade. In one aspect a plurality of bores are made which are distributed along the blade leaf center line.

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1. A method for the production of a coated turbine moving blade, comprising: coating a turbine moving blade with a protective layer; andintroducing a plurality of recesses into a blade tip of a blade leaf of the turbine moving blade, wherein the number and depth of the recesses are configured to com

1. A method for the production of a coated turbine moving blade, comprising: coating a turbine moving blade with a protective layer; andintroducing a plurality of recesses into a blade tip of a blade leaf of the turbine moving blade, wherein the number and depth of the recesses are configured to compensate a shift in characteristic frequency of the turbine moving blade produced by a mass of the protective layer,wherein the introduction of the plurality of recesses occurs after the coating of the turbine moving blade,wherein each of the plurality of recesses is a hole which is drilled into the blade tip in a direction of a blade foot of the turbine moving blade, andwherein the plurality of recesses are distributed along a center line of the blade leaf, the center line running centrally from a leading edge to a trailing edge of the blade leaf. 2. The method as claimed in claim 1, further comprising superficially closing the drilled recesses. 3. The method as claimed in claim 2, wherein the plurality of recesses are closed using a plug or solder, whereby each recess is partially filled up leaving a cavity. 4. The method as claimed in claim 1, wherein a drill depth is to 50% of a radial extent of the blade leaf with respect to an installation position of the turbine moving blade. 5. The method as claimed in claim 1, wherein prior to the step of coating, an existing coating is removed from the turbine moving blade. 6. The method as claimed in claim 1, wherein the protective layer comprises a corrosion protection layer and/or a heat insulation layer. 7. A method for the production of a coated turbine moving blade, comprising: coating a turbine moving blade with a protective layer; andintroducing a plurality of recesses into a blade tip of a blade leaf of the turbine moving blade, wherein the number and depth of the recesses are configured to compensate a shift in characteristic frequency of the turbine moving blade produced by a mass of the protective layer,wherein the introduction of the plurality of recesses occurs after the coating of the turbine moving blade,wherein each of the plurality of recesses is a hole which is drilled into the blade tip in a direction of a blade foot of the turbine moving blade, andwherein the plurality of recesses are distributed laterally with respect to a center line of the blade leaf, the center line running centrally from a leading edge to a trailing edge of the blade leaf. 8. The method as claimed in claim 7, further comprising superficially closing the drilled recesses. 9. The method as claimed in claim 8, wherein the plurality of recesses are closed using a plug or solder, whereby each recess is partially filled up leaving a cavity. 10. The method as claimed in claim 7, wherein the method is performed on a turbine moving blade having an internally coolable blade leaf. 11. The method as claimed in claim 7, wherein the plurality of recesses are made in a region of a trailing edge of the turbine moving blade where a suction-side pressure wall meets a delivery-side pressure wall. 12. The method as claimed in claim 7, wherein a drill depth is to 50% of a radial extent of the blade leaf with respect to an installation position of the turbine moving blade. 13. The method as claimed in claim 7, wherein prior to the step of coating, an existing coating is removed from the turbine moving blade. 14. The method as claimed in claim 7, wherein the protective layer comprises a corrosion protection layer and/or a heat insulation layer.