Patent ID: 9518738
Filing Date: 2016-12-13
CPC Classification: F23R

Claim Text:
1. A gas turbine combustion chamber, comprising: a combustion chamber wall including a tile carrier, a plurality of wall tiles mounted on the tile carrier spaced apart from the tile carrier to form an impingement cooling gap between the tile carrier and the plurality of wall tiles, wherein the tile carrier includes a plurality of impingement cooling holes and each wall tile includes a plurality of effusion holes with inlet openings, wherein each wall tile includes, on a side facing the tile carrier, a surface structure which includes raised portions rising from a surface of the wall tile and extending in a direction toward the tile carrier; wherein the inlet openings of the effusion holes are located on the raised portions of the surface structure; wherein the centric axes of the inlet openings are arranged substantially perpendicular to a surface of the tile carrier; wherein the centric axes of the inlet openings are arranged substantially parallel to centric axes of the impingement cooling holes; wherein the raised portions are formed as ribs; wherein the impingement cooling holes are arranged to direct impingement air jets into a space between the ribs and spaced apart from the inlet openings.