Combustion chamber cooling

[0032]FIG. 1 shows, schematically and by way of example, a gas turbine combustion chamber 1 according to the prior art with an inner wall 2 (burner liner) which encloses the combustion space 3 and has, on the combustion space side, a thermal protection coating 4, and a sheath 5 surrounding the inner wall 2. Between the inner wall and the sheath 5, cooling air 6 is guided for convectively cooling the inner wall 2. In the transition from the combustion space 3 downstream to the turbine space (not shown), the gas turbine combustion chamber 1 and therefore also the inner wall 2 or the burner liner 2 are conical. This region is therefore also termed the liner cone 7.

[0033]FIG. 2 shows a gas turbine combustion chamber 8 according to the invention with an inner wall 2 and an outer wall 9 spaced apart therefrom, which form a cavity 10 (see FIGS. 5 and 6). The outer wall 9 is formed by a plate construction, comprised of eight wall elements 11, which are configured and arranged and supported to