Turbulator structure on combustor liner

1. A method of cooling a hot gas wall for a gas turbine, the hot gas wall having a wall part with a front side and a back side, the wall part being configured for exposure to a hot fluid on the front side, the hot gas wall having a turbulator including a plurality of ribs attached to the back side of the wall part by a braze alloy placed between the turbulator structure and the back side of the wall part and subjected to brazing, and the hot gas wall having an impingement sheet arranged to direct a cooling fluid flow along the back side of the wall part, wherein the plurality of ribs form hexagons in a honeycomb structure, each rib having a height “h” being a distance from a side of the rib adjacent to the back side of the wall part to a side of the rib furthest from the back side of the wall part, each hexagon having a width “a” being a distance between a rib and a rib on an opposite side of the hexagon, each hexagon having a width “b” being a distance between a join of two ribs to a join of two ribs on an opposite side of the hexagon, wherein a ratio between the height “h” and a distance “H” being a distance between the back wall and the impingement sheet is between 0.01 and 0.3, a ratio between the width “a” and the height “h” is between 1 and 1 0 , and a ratio between the width “b” and the height “h” is between 1 and 10,

the method comprising:

directing a cooling fluid along the back side of the wall part.

2. A hot gas wall for a gas turbine, comprising:

a wall part with a front side and a back side, the wall part being configured for exposure to a hot fluid on the front side;

a turbulator including a plurality of ribs attached to the back side of the wall part by a braze alloy placed between the turbulator structure and the back side of the wall part and subjected to brazing; and

an impingement sheet arranged to direct a cooling fluid flow along the back side of the wall part, wherein the plurality of ribs form hexagons in a honeycomb structure, each rib having a height “h” being a distance from a side of the rib adjacent to the back side of the wall part to a side of the rib furthest from the back side of the wall part, each hexagon having a width “a” being a distance between a rib and a rib on an opposite side of the hexagon, each hexagon having a width “b” being a distance between a join of two ribs to a join of two ribs on an opposite side of the hexagon, wherein a ratio between the height “h” and a distance “H” being a distance between the back wall and the impingement sheet is between 0.01 and 0.3, a ratio between the width “a” and the height “h” is between 1 and 10, and a ratio between the width “b” and the height “h” is between 1 and 10.

3. The hot gas wall of claim 2 , wherein the wall part comprises:

a curved section and the turbulator structure is attached to the curved section of the wall part.

4. The hot gas wall of claim 3 , wherein the curved section is curved along a longitudinal direction denoted by a longitudinal axis and also curved in a plane perpendicular to the longitudinal axis.

5. The hot gas wall of claim 2 , wherein the turbulator is arranged in a honeycomb pattern.

6. The hot gas wall of claim 2 , in which the plurality of ribs of the turbulator comprise:

a first set of ribs parallel to one another and a second set of ribs parallel to one another and not parallel to the first set of ribs, wherein the turbulator structure is configured to be orientated such that a cooling flow direction is parallel to the first set of ribs, or such that the cooling flow direction is at the same angle from the first set of ribs and the second set of ribs.

7. A gas turbine or a gas turbine combustor comprising:

the hot gas wall of claim 2 .