Turbulator structure on combustor liner

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 10, 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.