Abstract: A combustion chamber (4) of a gas turbine (1), the combustion space (24) of which is bounded by an annular combustion chamber inner wall (28) and a combustion chamber outer wall (26), in which in order to generate a working medium (M) a supplied fuel is brought into reaction with supplied combustion air, and the combustion chamber wall (25) of which is provided on the inside with a lining formed from a plurality of heat shield elements (38), with the or each heat shield element (38) together with the combustion chamber wall (25) forming an inner space (40) to which a cooling medium (K) can be applied, is to be designed so as to provide a high level of system efficiency at the same time as having a comparatively simple structure and it should also be possible to disassemble the combustion chamber inner wall (28) in a time-saving manner.

Abstract: In a gas turbine (1) with an annular combustion chamber (4), the combustion area (24) of which is bounded by an annular combustion chamber outer wall (26) on the one hand and by an annular combustion chamber inner wall (28) located therein on the other hand, it should be possible to dismantle the combustion chamber inner wall (28) comparatively quickly and easily. For this purpose according to the invention the combustion chamber inner wall (28) is formed by a plurality of wall elements attached to a support structure, wherein the support structure is formed by a plurality of sub-components abutting each other at a horizontal parting joint and the abutting sub-components (30) of the combustion chamber inner wall (28) are connected to each other at their horizontal parting joint by means of a plurality of screw connections (32) oriented at an angle to the inner wall surface.

Abstract: The invention relates to a gas turbine comprising a combustion chamber, into which fuel and combustion air are fed and caused to react, in order to produce a working fluid. The aim of the invention is to provide a particularly simple construction, which achieves a relatively high degree of efficiency for the installation. To achieve this, the inventive combustion chamber can be cooled and has a tubular structure, the combustion chamber wall being composed of coolant pipes.

Abstract: In a gas turbine (1) with an annular combustion chamber (4), the combustion area (24) of which is bounded by an annular combustion chamber outer wall (26) on the one hand and by an annular combustion chamber inner wall (28) located therein on the other hand, it should be possible to dismantle the combustion chamber inner wall (28) comparatively quickly and easily. For this purpose according to the invention the combustion chamber inner wall (28) is formed by a plurality of wall elements attached to a support structure, wherein the support structure is formed by a plurality of sub-components abutting each other at a horizontal parting joint and the abutting sub-components (30) of the combustion chamber inner wall (28) are connected to each other at their horizontal parting joint by means of a plurality of screw connections (32) oriented at an angle to the inner wall surface.

Abstract: A combustion chamber (4) of a gas turbine (1), the combustion space (24) of which is bounded by an annular combustion chamber inner wall (28) and a combustion chamber outer wall,(26), in which in order to generate a working medium (M) a supplied fuel is brought into reaction with supplied combustion air, and the combustion chamber wall (25) of which is provided on the inside with a lining formed from a plurality of heat shield elements (38), with the or each heat shield element (38) together with the combustion chamber wall (25) forming an inner space (40) to which a cooling medium (K) can be applied, is to be designed so as to provide a high level of system efficiency at the same time as having a comparatively simple structure and it should also be possible to disassemble the combustion chamber inner wall (28) in a time-saving manner.

Abstract: A gas turbine is provided which has a combustor comprising a plurality of can-type combustor elements and an annular element. Isolated combustion takes place in the can-type combustor thereby generating individual component hot gas streams. The component hot gas streams are merged in the annular part. Combustion oscillations are substantially avoided by decoupling combustion flames. Accordingly, temperature and pressure homogenization as well as combustion stabilization by cross-ignition is effected.

Abstract: A heat-shield component with a cooling-fluid return, a hot-gas wall to be cooled, an inlet duct for conducting a cooling fluid and an outlet duct for returning the cooling fluid. The inlet duct is directed towards the hot-gas wall and widens in a direction of the hot-gas wall. Furthermore, the invention relates to a heat-shield configuration which lines a component directing a hot gas, in particular a combustion chamber of a gas-turbine plant. The heat-shield configuration and has a plurality of the heat-shield components.

Abstract: A heat shield assembly includes a supporting structure having an outer surface to be shielded from a hot fluid, the supporting structure having cooling fluid ducts formed therein; and an internal lining formed of heat-resistant material, the internal lining including mutually adjacent mushroom-shaped heat shield elements each having a cap portion in the form of a polygonal plate body having a central region, the plate bodies each covering a portion of the outer surface of the supporting structure and defining cooling fluid gaps therebetween, and a shaft portion thermally moveably anchoring the central region of the plate body to the supporting structure.