Patent ID: 8099961

Claim:
A gas-turbine combustion chamber wall for a gas-turbine comprising: a combustion chamber wall; a plurality of tiles arranged on an inner side of the combustion chamber wall, with an interspace being formed between the tiles and the combustion chamber wall; impingement-cooling holes provided in the combustion chamber wall for introducing cooling air into the interspace; effusion-cooling holes provided in the tiles through which cooling air from the interspace flows into a combustion chamber; wherein the tiles include a surface structure on a side facing the combustion chamber wall; wherein an area provided with the impingement-cooling holes, an area provided with the surface structure and an area provided with effusion-cooling holes are offset relative to each other in an axial direction of the combustion chamber such that there are four regions progressing in consecutive numeric order in the axial direction in a direction of combustion gas flow from first to fourth, each region having an axial extent and an inward/outward extent that encompasses both the combustion chamber wall and the inwardly arranged tiles along the axial extent, the four regions being a first region of only impingement cooling holes, a second region of overlap of impingement cooling holes and the surface structure, a third region of overlap of effusion cooling holes and the surface structure and a fourth region of only effusion cooling holes.