Heat shield segment for a stator of a gas turbine

1. A gas turbine comprising:

a turbine housing;

a rotatable turbine rotor having a plurality of turbine blades; and

at least one heat shield segment for a stator disposed radially between the rotor and the housing and attached to the housing, the at least one heat shield segment having a profile with a curved section in at least one region in an axial direction of the gas turbine and having a radial outer surface and including:

a first boss extending in a circumferential direction of the gas turbine in a region of the curved section and in a first end area in the circumferential direction disposed on the radial outer surface;

a rib disposed at the first end area extending at least partially in a longitudinal direction of the gas turbine, wherein the first boss protrudes from the rib in the circumferential direction disposed on the radial outer surface; and

a second boss extending in the circumferential direction in a region of the curved section and in a second area opposite to the first end area disposed on the radial outer surface, wherein the profile includes a two-stepped form in the circumferential direction in an area of the first boss, wherein a first step extends from the radial outer surface to the first boss and a second step extends from the first boss to the rib.

2. The gas turbine as recited in claim 1 , wherein a length of the first boss in the circumferential direction is less than a quarter of a total length of the at least one heat shield segment in the circumferential direction.

3. The gas turbine as recited in claim 1 , wherein a ratio of a length of the first boss in the circumferential direction to a width of the at least one boss in the axial direction is between 1:2 and 3:1.

4. The gas turbine as recited in claim 1 , wherein the profile includes a second curved section in the axial direction, wherein the second curved section includes at least one of another first boss in a first end region in the circumferential direction on the radial outer surface extending in the circumferential direction and another second boss disposed in a second end region in the circumferential direction on the radial outer surface and extending in the circumferential direction.

5. The gas turbine as recited in claim 1 , wherein an inner profile of the at least one heat shield segment includes a first section extending parallel to the axial direction and a second section upstream of the first section extending at an angle to the axial direction, wherein the first boss is disposed at a position wherein the first and the second sections meet in the axial direction.

6. The gas turbine as recited in claim 1 , wherein the at least one heat shield segment includes a groove disposed in an area of the first boss and in a radially extending side of the at least one heat shield segment and extending in the axial direction.

7. The gas turbine as recited in claim 1 , wherein the at least one heat shield segment includes a plurality of heat shield segments forming a heat shield of an outer limit of a hot gas flow along the turbine blades.

8. A heat shield segment for a stator of a gas turbine disposed radially between a turbine rotor and turbine housing and attached to the housing having a profile with a curved section in at least one region in an axial direction of the gas turbine and having a radial outer surface comprising:

a first boss extending in a circumferential direction of the gas turbine in a region of the curved section and in a first end area in the circumferential direction disposed on the radial outer surface of the at least one heat shield segment;

a rib disposed at the first end area extending at least partially in a longitudinal direction of the gas turbine, wherein the first boss protrudes from the rib in the circumferential direction disposed on the radial outer surface; and

a second boss extending in the circumferential direction in a region of the curved section and in a second area opposite to the first end area disposed on the, radial outer surface, wherein the profile includes a two-stepped form in the circumferential direction in an area of the first boss, wherein a first step extends from the radial outer surface to the first boss and a second step extends from the at least one boss to the rib.

9. The heat shield segment as recited in claim 8 , wherein a length of the first boss in the circumferential direction is less than a quarter of a total length of the heat shield segment in the circumferential direction.

10. The heat shield segment as recited in claim 8 , wherein a ratio of a length of the first boss in the circumferential direction to a width of the at least one boss in the axial direction is between 1:2 and 3:1.

11. The heat shield segment as recited in claim 8 , wherein the profile includes a second curved section in the axial direction, wherein the second curved section includes at least one of another first boss in a first end region in the circumferential direction on the radial outer surface extending in the circumferential direction and another second boss disposed in a second end region in the circumferential direction on the radial outer surface and extending in the circumferential direction.

12. The heat shield segment as recited in claim 8 , wherein the profiled includes an inner profile having a first section extending parallel to the axial direction and a second section upstream of the first section extending at an angle to the axial direction, wherein the first boss is disposed at a position wherein the first and the second sections meet in the axial direction.

13. The heat shield segment as recited in claim 8 , further comprising a groove disposed in an area of the first boss and in a radially extending side of the heat shield segment and extending in the axial direction.

14. The heat shield segment as recited in claim 8 , wherein the at least one heat shield segment includes a plurality of heat shield segments forming a heat shield of an outer limit of a hot gas flow along the turbine blades.