for example electron beam deposition eb pvd other coating methods may be envisaged for example atmospheric plasma spraying aps lpps vps or cvd the thermal barrier layer may comprise porous micro or macro cracked grains for better thermal shock resistance the thermal barrier layer is thus preferably more porous than the mcralx layer the blade 120 130 may be designed to be hollow or solid if the blade 120 130 is intended to be cooled it will be hollow and optionally also comprise film cooling holes 418 indicated by dashes fig5 shows a combustion chamber 110 of the gas turbine 100 the combustion chamber 110 is designed for example as a so called ring combustion chamber in which a multiplicity of burners 107 which produce flames 156 and are arranged in the circumferential direction around a rotation axis 102 open into a common combustion chamber space 154 to this end the combustion chamber 110 as a whole is designed as an annular structure which is positioned around the rotation axis 102 in order to achieve a comparatively high efficiency the combustion chamber 110 is designed for a relatively high temperature of the working medium m of about 1000 u00b0 c to 1600 u00b0 c in order to permit a comparatively long operating time even under these operating parameters which are unfavorable for the materials the combustion chamber wall 153 is provided with an inner lining formed by heat shield elements 155 on its side facing the working medium m owing to the high temperatures inside the combustion chamber 110 a cooling system may also be provided for the heat shield elements 155 or for their retaining elements the heat shield elements 155 are then hollow for example and.