Method for producing a cavity in a blade platform; corresponding blade
A method for producing a cavity in a blade platform of a blade, in particular of a turbine blade, as part of a blade-platform cooling system, wherein the method has the steps of: producing a first bore from a first platform lateral face in the direction of an opposite second platform lateral face, with a first opening in the first platform lateral face being created, and expanding the first bore in a fan-like manner by an electrical discharge machining method, in particular using a wire- or bar-form electrode, such that the first opening, created in the first step, of the first bore represents the starting point of the fan-like expansion. A blade is produced in particular with such a method.
1. A method for producing a cavity in a blade platform of a blade, the method comprising:
a) producing a first bore starting from a first platform side surface in the direction of an opposite second platform side surface, generating a first opening in the first platform side surface, and
b) widening the first bore in the manner of a fan by a spark erosion method, in such a way that the first opening, generated in step a), of the first bore represents the starting point of a segment of a circle in the form of an arc widening,
wherein, in step b), starting from the first opening of the first bore, a plurality of further bores are generated which each has a predetermined angular offset with respect to one another, wherein bores adjacently arranged overlap each other in some regions, or
wherein, in step b), a rigid electrode is inserted into the first opening of the first bore for the spark erosion method and is pivoted in the arc fashion.
2. The method as claimed in claim 1 ,
wherein the depth of the first bore and/or the further bores in each case extends beyond an imaginary central plane between the first platform side surface and the second platform side surface.
3. The method as claimed in claim 1 ,
wherein a bore is produced which generates a second opening in the first platform side surface and/or in the second platform side surface and which extends, starting from this second opening, toward the opposite platform side surface, and
wherein the bore is widened in the arc fashion by the spark erosion method, in such a way that the second opening represents the starting point of the arc widening.
4. The method as claimed in claim 3 ,
wherein, as part of the arc widening, starting from the second opening generated in the first or second platform side surface, a plurality of further bores are generated which each has a predetermined angular offset relative to one another, wherein adjacently arranged bores overlap one another in some regions, or
wherein, as part of the arc widening, the rigid electrode is inserted into the bore starting from the second opening for the spark erosion method and is pivoted in the arc fashion.
5. The method as claimed in claim 4 ,
wherein the depth of the bore or the further bores in each case extends beyond an imaginary central plane between the second platform side surface and the first platform side surface.
6. The method as claimed in claim 3 ,
wherein the arc widening effected by the same or different platform side surface defines a common cavity.
7. The method as claimed in claim 1 ,
wherein at least the blade platform is produced from a super alloy, or a nickel-based super alloy.
8. The method of claim 1 ,
wherein the blade comprises a turbine blade as part of a blade platform cooling system.
9. The method of claim 1 ,
wherein the spark erosion method comprises using the rigid electrode in the form of a wire or rod.