the gas turbine 1 according to fig1 has a compressor 2 for combustion air , a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator ( not shown ) or a driven machine . to this end , the turbine 6 and the compressor 2 are arranged on a common shaft 8 , which is also referred to as turbine rotor and to which the generator or the driven machine is also connected and which is rotatably mounted about its center axis 9 . the combustion chamber 4 , designed like an annular combustion chamber , is fitted with a number of burners 10 for burning a liquid or gaseous fuel . the turbine 6 has a number of rotatable moving blades 12 connected to the turbine shaft 8 . the moving blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of moving blade rows . furthermore , the turbine 6 comprises a number of fixed guide blades 14 , which are likewise fastened in a ring shape to an inner casing 16 of the turbine 6 while forming guide blade rows . in this case , the moving blades 12 serve to drive the turbine shaft 8 by impulse transmission from the working medium m flowing through the turbine 6 . the guide blades 14 , on the other hand , serve to direct the flow of the working medium m between in each case two moving blade rows or moving blade rings following one another as viewed in the direction of flow of the working medium m . a successive pair consisting of a ring of guide blades 14 or a guide blade row and of a ring of moving blades 12 or a moving blade row is in this case referred to as turbine stage . each guide blade 14 has a platform 18 which is referred to as blade root and is arranged as a wall element for fixing the respective guide blade 14 on the inner casing 16 of the turbine 6 . in this case , the platform 18 is a component which is subjected to comparatively high thermal loading and forms the outer boundary of a hot - gas duct for the working medium m flowing through the turbine 6 . each moving blade 12 is fastened to the turbine shaft 8 in a similar manner via a platform 20 referred to as blade root . a guide ring 21 is in each case arranged on the inner casing 16 of the turbine 6 between the platforms 18 , arranged at a distance from one another , of the guide blades 14 of two adjacent guide blade rows . here , the outer surface of each guide ring 21 is likewise exposed to the hot working medium m flowing through the turbine 6 and is kept at a radial distance from the outer end 22 of the moving blade 12 lying opposite it by means of a gap . in this case , the guide rings 21 arranged between adjacent guide blade rows serve in particular as cover elements which protect the inner wall 16 or other built - in casing components from thermal overstressing by the hot working medium m flowing through the turbine 6 . in the exemplary embodiment , as shown in fig2 , the combustion chamber 4 is configured as an “ annular combustion chamber ”, in which a multiplicity of burners 10 arranged in the circumferential direction around the turbine shaft 8 open out into a common combustion chamber space . to this end , the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8 . to achieve a comparatively high efficiency , the combustion chamber 4 is designed for a comparatively high temperature of the working medium m of about 1200 ° c . to 1500 ° c . in order to also permit a comparatively long operating period with these operating parameters , which are unfavorable for the materials , the combustion chamber wall 24 is provided on its side facing the working medium m with an inner lining formed from heat shield elements 26 . on account of the high temperatures in the interior of the combustion chamber 4 , a cooling system is provided for the heat shield elements 26 . the heat shield elements 26 are designed in particular for a long service life , so that as little damage as possible occurs due to the external effects , such as the high temperature and vibrations of the combustion chamber 4 . to this end , said heat shield elements 26 consist of a basic body 28 which is formed from a cast ceramic material and in which reinforcing elements 30 are integrated . for suitable thermal stability of the reinforcing elements , they are made of a ceramic material or a composite material . to this end , the reinforcing elements 30 can be designed for the effects acting on the heat shield element 26 . various embodiments of heat shield elements 26 with reinforcing elements 30 are presented in fig3 to 7 . a heat shield element 26 with plate - shaped reinforcing elements 30 is shown in fig3 , a reinforcing element 30 being provided in each case for the surface facing the working medium m and the surface facing the cooled side . it can be seen in fig4 that the plate - shaped reinforcing elements 30 , for a better bond with the surrounding ceramic , may be provided with a lattice - shaped structure or may be designed as a lattice , in particular as a cross lattice ( fig4 a ) or as a perforated lattice ( fig4 b ). for especially pronounced reinforcement of the marginal regions of a heat shield element 26 , rod - shaped reinforcing elements 30 may be used , as shown in fig5 , these rod - shaped reinforcing elements 30 running along the side edges of a heat shield element 26 and being provided with beads or thickened portions ( fig5 a ) or thickened ends ( fig5 b ) in order to ensure firm anchoring in the surrounding ceramic 28 . it can be seen from fig6 that an annular structure ( fig6 a ) of the reinforcing elements 30 may be used for reinforcement of a heat shield element 26 along its periphery , in which case , in an especially torsionally rigid embodiment , this annular structure may be of circular design ( fig6 b ). in the heat shield element 26 shown in fig7 , a cross - shaped reinforcing element 30 is provided in order to brace the corners of a heat shield element 26 in a stabilizing manner , this cross - shaped reinforcing element 30 having thickened portions at each of its ends for anchoring in the ceramic material 26 .