Turbine vane

1. A stator for a turbine comprising:

an arrangement of vanes including at least a first vane and a second vane circumferentially neighbouring the first vane, each of the first vane and the second vane comprising:

an airfoil;

a channel system configured to cool each respective vane with cooling gas; and

an inner diameter platform disposed at an inner end of the airfoil, the inner diameter platform including an inner diameter platform cavity and at least one circumferentially arranged side wall which delimits the inner diameter platform cavity, the inner diameter platform cavity being connected with the channel system so as to feed the cooling gas to the inner diameter platform;

at least one sealing plate disposed between the at least one circumferentially arranged side wall of the first vane and the at least one circumferentially arranged side wall of the second vane, the at least one circumferentially arranged side walls of the first vane and the second vane facing one another, so as to form an intermediate cavity that is fluidically separated from the inner diameter platform cavity;

wherein the at least one sealing plate forms a peripheral sealing that at least substantially encloses the intermediate cavity;

wherein the peripheral sealing includes at least one opening that is disposed at a bottom side of the intermediate cavity, which is a radially furthest away side from the airfoil, and that is configured as a gas inlet; and

wherein the at least one opening has a circular shape.

2. The stator according to claim 1 , wherein the turbine is a gas turbine.

3. The stator according to claim 1 , wherein the inner diameter platform of at least one of the first vane and the second vane includes at least one groove disposed around a region of the intermediate cavity, the at least one sealing plate being disposed in the at least one groove.

4. The stator according to claim 1 , wherein the at least one opening is fluidically separated from the channel systems of the first vane and the second vane.

5. The stator according to claim 1 , comprising:

a ring shaped sealing disposed on an underside of a bottom plate of the inner diameter platform, the bottom plate being disposed on a side of the inner diameter platform cavity that is furthest away from the airfoil.

6. The stator according to claim 5 , wherein the ring shaped sealing is a Del Matto sealing.

7. The stator according to claim 1 , wherein, for each of the first vane and the second vane, the channel system includes at least one channel extending within the airfoil and connected to an outer diameter platform cavity disposed at a radially outer end of the airfoil of a respective one of the vanes.

8. The stator according to claim 1 , wherein, for each of the first vane and the second vane, the inner diameter platform includes at least one gas outlet.

9. The stator according to claim 8 , wherein the at least one gas outlet is disposed on a side of the inner diameter platform facing the airfoil.

10. The stator according to claim 1 , comprising:

a ring shaped sealing disposed on an underside of a bottom plate of the inner diameter platform, the bottom plate being disposed on a side of the inner diameter platform cavity that is furthest away from the airfoil.

11. The stator according to claim 10 , wherein the ring shaped sealing is a Del Matto sealing.

12. A stator for a turbine comprising:

an arrangement of vanes including at least a first vane and a second vane circumferentially neighbouring the first vane, each of the first vane and the second vane comprising:

an airfoil:

a channel system configured to cool each respective vane with cooling gas; and

an inner diameter platform disposed at an inner end of the airfoil, the inner diameter platform including an inner diameter platform cavity and at least one circumferentially arranged side wall which delimits the inner diameter platform cavity, the inner diameter platform cavity being connected with the channel system so as to feed the cooling gas to the inner diameter platform;

at least one sealing plate disposed between the at least one circumferentially arranged side wall of the first vane and the at least one circumferentially arranged side wall of the second vane, the at least one circumferentially arranged side walls of the first vane and the second vane facing one another, so as to form an intermediate cavity that is fluidically separated from the inner diameter platform cavity;

wherein the at least one sealing plate forms a peripheral sealing that at least substantially encloses the intermediate cavity;

wherein the peripheral sealing includes at least one opening that is disposed at a bottom side of the intermediate cavity, which is a radially furthest away side from the airfoil, and that is configured as a gas inlet; and

wherein the inner diameter platform of at least one of the first vane and the second vane includes at least one groove disposed around a region of the intermediate cavity, the at least one groove including an interruption that is aligned with or forms part of a boundary of the at least one opening.

13. The stator according to claim 12 , wherein the turbine is a gas turbine.

14. The stator according to claim 12 , wherein the inner diameter platform of at least one of the first vane and the second vane includes at least one groove disposed around a region of the intermediate cavity, the at least one sealing plate being disposed in the at least one groove.

15. The stator according to claim 12 , wherein the at least one opening is fluidically separated from the channel systems of the first vane and the second vane.

16. The stator according to claim 12 , wherein the at least one opening has a symmetrical shape.

17. The stator according to claim 12 , wherein, for each of the first vane and the second vane, the channel system includes at least one channel extending within the airfoil and connected to an outer diameter platform cavity disposed at a radially outer end of the airfoil of a respective one of the vanes.

18. The stator according to claim 12 , wherein, for each of the first vane and the second vane, the inner diameter platform includes at least one gas outlet, and

wherein the at least one gas outlet is disposed on a side of the inner diameter platform facing the airfoil.

19. A turbine comprising:

a rotor; and

at least one stator comprising:

an arrangement of vanes including at least a first vane and a second vane circumferentially neighbouring the first vane, each of the first vane and the second vane comprising: an airfoil;

a channel system configured to cool each respective vane with cooling gas; and

an inner diameter platform disposed at an inner end of the airfoil, the inner diameter platform including an inner diameter platform cavity and at least one circumferentially arranged side wall which delimits the inner diameter platform cavity, the inner diameter platform cavity being connected with the channel system so as to feed the cooling gas to the inner diameter platform, and at least one sealing plate disposed between the at least one circumferentially arranged side wall of the first vane and the at least one circumferentially arranged side wall of the second vane, the at least one circumferentially arranged side walls of the first vane and the second vane facing one another, so as to form an intermediate cavity that is fluidically separated from the inner diameter platform cavity;

wherein the at least one sealing plate forms a peripheral sealing that at least substantially encloses the intermediate cavity;

wherein the peripheral sealing includes at least one opening that is disposed at a bottom side of the intermediate cavity, which is a radially furthest away side from the airfoil, and that is configured as a gas inlet; and

wherein the inner diameter platform of at least one of the first vane and the second vane includes at least one groove disposed around a region of the intermediate cavity, the at least one groove including an interruption that is aligned with or forms part of a boundary of the at least one opening.

20. The turbine according to claim 19 , wherein the turbine is a gas turbine.