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: 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: A thermal shielding brick is useable for lining a combustion chamber wall. The thermal shielding brick has a hot side, which can be exposed to a hot medium a wall side located opposite the hot side, and a peripheral side that is joined to the hot side and to the wall side. A damping element is placed on the peripheral side and effectively prevents fragments from detaching from the thermal shielding brick if broken. A combustion chamber having an inner combustion chamber lining, includes the thermal shielding bricks. Further, a gas turbine, includes the combustion chamber.

Abstract: The invention relates to a heat-shield brick, in particular for lining a combustion chamber wall, comprising a hot side that can be exposed to a hot medium, a wall side that lies opposite said hot side and a peripheral side that lies adjacent to the hot side and the wall side and that has peripheral lateral face. A tensioning element, pre-stressed in the peripheral direction is provided on the peripheral side, whereby a compressive stress generated perpendicularly to the peripheral lateral face. The invention also relates to a combustion chamber comprising a combustion chamber lining, which has heat-shield bricks of this type and to a gas turbine comprising a combustion chamber.

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: The invention relates to a heat-shield brick (1), in particular for lining a combustion chamber wall, comprising a hot side (3) that can be exposed to a hot medium, a wall side (5) that lies opposite said hot side (3) and a peripheral side (7) that lies adjacent to the hot side (3) and the wall side (5) and that has a peripheral lateral face (9). A tensioning element (11), pre-stressed in the peripheral direction is provided on the peripheral side (7), whereby a compressive stress is generated perpendicularly to the peripheral lateral face. The invention also relates to a combustion chamber comprising a combustion chamber lining, which has heat-shield bricks of this type and to a gas turbine comprising a combustion chamber.

Abstract: The invention relates to a thermal shielding brick (1, 1A, 1B), especially for lining a combustion chamber wall. Said thermal shielding brick has a hot side (5), which can be exposed to a hot medium, a wall side (7) located opposite said hot side (5), and a peripheral side (69) that is joined to the hot side and to the wall side. A damping element (3, 3A, 3B) is placed on the peripheral side and effectively prevents fragments (81,81A) from detaching from the thermal shielding brick (1, 1A, 1B) if broken. The invention also relates to a combustion chamber having an inner combustion chamber lining, which comprises said thermal shielding bricks (1, 1A, 1B), and to a gas turbine with a combustion chamber.