Frame segment for a combustor turbine interface

1. A frame segment for receiving an aft end, in a hot gas flow path direction, of a combustor transition piece for a gas turbine, the frame segment comprising:

an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web extending between the upper horizontal element and the lower horizontal element, wherein the vertical web is made of a U-profile with a base and two legs extending from the base wherein the base of the U-profile is a downstream face of the vertical web in the hot gas flow path direction, and wherein the two legs delimit a cooling gas duct.

2. The frame segment according to claim 1 , wherein the vertical web comprises:

a central beam which is enclosed by the U-profile, and wherein a gap between the central beam and the U-profile forms the cooling gas duct.

3. The frame segment according to claim 2 , wherein a cooling cavity is arranged as an impingement chamber and wherein the cooling gas duct opens towards the cooling cavity to impingement cool a heat shield.

4. The frame segment according to claim 1 , comprising:

a web extension configured to extend parallel to a combustor transition side wall in an axial direction beyond the downstream end of the combustor transition piece and into an upstream end of a turbine.

5. The frame segment according to claim 1 , wherein the cooling gas duct has a defined volume and a neck configured as a Helmholtz damper.

6. The frame segment according to claim 1 , wherein the cooling gas duct extends from the upper horizontal element to the lower horizontal element.

7. The frame segment according to claim 1 , wherein the vertical web comprises:

effusion cooling holes extending from the cooling gas duct through the downstream face.

8. The frame segment according to claim 1 , wherein the downstream face is covered with a thermal barrier coating.

9. The frame segment according to claim 1 , comprising:

a heat shield on the downstream face.

10. The frame segment according to claim 9 , wherein the heat shield extends over sides of a supporting structure of the vertical web in a plane parallel to the downstream face.

11. The frame segment according to claim 9 , wherein the heat shield is made of a high temperature alloy or ceramic material.

12. The frame segment according to claim 9 , wherein a cooling cavity is arranged in the vertical web behind the heat shield.

13. The frame segment according to claim 2 , wherein a cooling gas supply hole is radially extending from the cooling gas duct through the upper horizontal element and/or the lower horizontal element.

14. A gas turbine with at least one compressor, at least one turbine, and at least one combustion chamber with a combustor transition piece, comprising:

the frame segment according to claim 1 .

15. The frame segment according to claim 2 , comprising:

a web extension configured to extend parallel to a combustor transition side wall in an axial direction beyond the downstream end of the combustor transition piece and into an upstream end of a turbine.

16. The frame segment according to claim 2 , wherein the cooling gas duct has a defined volume and a neck configured as a Helmholtz damper.

17. The frame segment according to claim 2 , wherein the cooling gas duct extends from the upper horizontal element to the lower horizontal element.

18. The frame segment according to claim 2 , wherein the vertical web comprises:

effusion cooling holes extending from the cooling gas duct through the downstream face.

19. The frame segment according to claim 2 , wherein the downstream face is covered with a thermal barrier coating.

20. The frame segment according to claim 2 , comprising:

a heat shield on the downstream face.