Turbomachine component

1. A turbomachine component, comprising:

a basic component including a first outer wall having a first joint face;

an additional part including a second outer wall having a second joint face, wherein the first and the second wall enclose an internal cavity, and wherein the first and the second joint faces butt against each other and are joined together in a materially bonding manner so as to form a joint region between the basic component and the additional part;

at least one wall-like intermediate piece disposed in at least one of the basic component and the additional part and extending from the respective outer wall into the internal cavity, the at least one wall-like intermediate piece including a cutout having a transition contour that deviates from a straight line and is disposed at at least one transition between the at least one wall-like intermediate piece and the outer wall so as to relieve at least one of a mechanical and a thermal stress;

wherein the transition contour is recessed relative to the respective first or second joint face, is set-back from an inner side of the respective outer wall, and wherein at a predetermined distance from the outer wall, the transition contour returns to a level of the joint face.

2. The turbomachine component as recited in claim 1 , wherein the at least one wall-like intermediate piece includes a first intermediate piece disposed in the basic component and a second intermediate piece disposed in the additional part, and wherein the first intermediate piece and the second intermediate piece are aligned with each other and butt against each other at the joint region.

3. The turbomachine component as recited in claim 2 , wherein the basic component and the additional part are joined together in a materially bonding manner at a region of the intermediate pieces.

4. The turbomachine component as recited in claim 1 , wherein the at least one wall-like intermediate piece extends through the internal cavity between two opposite sections of the respective outer walls.

5. The turbomachine component as recited in claim 1 , wherein the additional part is configured as a replacement for material removed from the basic component.

6. The turbomachine component as recited in claim 1 , wherein the additional part is configured to widen the basic component.

7. The turbomachine component as recited in claim 1 , wherein the basic component and the additional part include a same material.

8. The turbomachine component as recited in claim 1 , wherein the basic component and the additional part are joined using at least one of a weld, a hard soldering and an adhesive fastening.

9. The turbomachine component as recited in claim 1 , wherein the turbomachine component is a turbine blade.

10. The turbomachine component as recited in claim 1 , wherein the transition contour returns to the level of the joint face in an arc.

11. The turbomachine component as recited in claim 10 , wherein the arc includes a quarter circle.

12. The turbomachine component as recited in claim 1 , wherein the transition contour returns to the level of the joint face in a linear gradient.

13. The turbomachine component as recited in claim 1 , wherein the transition contour returns to the level of the joint face in a step-like manner.

14. A turbomachine component, comprising:

a basic component including a first outer wall having a first joint face;

an additional part including a second outer wall having a second joint face, wherein the first and the second wall enclose an internal cavity, and wherein the first and the second joint faces butt against each other and are joined together in a materially bonding manner so as to form a joint region between the basic component and the additional part;

at least one wall-like intermediate piece disposed in at least one of the basic component and the additional part and extending from the respective outer wall into the internal cavity, the at least one wall-like intermediate piece including a cutout having a transition contour that deviates from a straight line and is disposed at at least one transition between the at least one wall-like intermediate piece and the outer wall so as to relieve at least one of a mechanical and a thermal stress;

wherein the transition contour is recessed relative to the respective first or second joint face, is entirely disposed at a level that is lower than the joint face, and includes an arc-like transition to the lower level.

15. A turbomachine component, comprising:

a basic component including a first outer wall having a first joint face;

an additional part including a second outer wall having a second joint face, wherein the first and the second wall enclose an internal cavity, and wherein the first and the second joint faces butt against each other and are joined together in a materially bonding manner so as to form a joint region between the basic component and the additional part;

at least one wall-like intermediate piece disposed in at least one of the basic component and the additional part and extending from the respective outer wall into the internal cavity, the at least one wall-like intermediate piece including a cutout having a transition contour that deviates from a straight line and is disposed at at least one transition between the at least one wall-like intermediate piece and the outer wall so as to relieve at least one of a mechanical and a thermal stress;

wherein the transition contour is recessed relative to the respective first or second joint face, is entirely disposed at a level that is lower than the joint face, and wherein the transition contour includes a linear transition to the lower level.

16. A turbomachine component, comprising:

a basic component including a first outer wall having a first joint face;

an additional part including a second outer wall having a second joint face, wherein the first and the second wall enclose an internal cavity, and wherein the first and the second joint faces butt against each other and are joined together in a materially bonding manner so as to form a joint region between the basic component and the additional part; and

at least one wall-like intermediate piece disposed in at least one of the basic component and the additional part and extending from the respective outer wall into the internal cavity, the at least one wall-like intermediate piece including a cutout having a transition contour that deviates from a straight line and is disposed at at least one transition between the at least one wall-like intermediate piece and the outer wall so as to relieve at least one of a mechanical and a thermal stress;

wherein the at least one wall-like intermediate piece includes a first intermediate piece disposed in the basic component and a second intermediate piece disposed in the additional part, and wherein the first intermediate piece and the second intermediate piece are aligned with each other and butt against each other at the joint region; and

wherein the first intermediate piece and the second intermediate piece butt against each other at the joint region by a butt joint having a cross-sectional contour that deviates from a straight line oriented perpendicularly to the intermediate pieces so as to reduce flow turbulences occurring at the butt joint.

17. The turbomachine component as recited in claim 16 , wherein the cross-sectional contour is linear and disposed obliquely to the intermediate pieces.

18. The turbomachine component as recited in claim 16 , wherein the cross-sectional contour is V-shaped.

19. The turbomachine component as recited in claim 16 , wherein the cross-sectional contour is arc-shaped.