Abstract: A thermal shield stone for covering the wall of a combustion chamber. The stone includes a hot side which can be exposed to a hot medium and a wall side which is arranged opposite the hot side. A hot side area adjoins the hot side. The wall side adjoins a wall side area. The average particle size in the wall side area is smaller than in the hot side area.

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: Disclosed is a lining for inner walls of combustion chambers having essentially plate-shaped shielding elements arranged on the inner walls so as to leave a gap. To introduce efficient sealing off against the penetration of hot gases, porous flow barriers capable of being inserted into the gap between adjacent shielding elements are used. The flow barriers are effective in reducing the air demand. The reduction in the air demand has a positive effect on the stability of the burner flames, the effectiveness of the machine and the pollutant emissions and makes it possible to have a further increase in performance, while adhering to maximum given material temperatures.

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: The invention relates to a heat shield block, in particular for lining a combustion chamber wall, having a hot side which can be subjected to a hot medium, a wall side opposite the hot side, and a peripheral side adjoining the hot side and the wall side. A tension element which can be prestressed to a prestress (Fz) is attached to the peripheral side, release of a fragment, formed during a fracture, of the heat shield block being reliably prevented by the prestress (Fz) of the tension element. The invention also relates to the use of a heat shield block, in particular for lining a combustion chamber wall of a gas turbine.

Abstract: A thermal shield stone for covering the wall of a combustion chamber. The stone includes a hot side which can be exposed to a hot medium and a wall side which is arranged opposite the hot side. A hot side area adjoins the hot side. The wall side adjoins a wall side area. The average particle size in the wall side area is smaller than in the hot side area.

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.

Abstract: Disclosed is a lining for inner walls of combustion chambers having essentially plate-shaped shielding elements arranged on the inner walls so as to leave a gap. To introduce efficient sealing off against the penetration of hot gases, porous flow barriers capable of being inserted into the gap between adjacent shielding elements are used. The flow barriers are effective in reducing the air demand. The reduction in the air demand has a positive effect on the stability of the burner flames, the effectiveness of the machine and the pollutant emissions and makes it possible to have a further increase in performance, while adhering to maximum given material temperatures.

Abstract: The invention relates to a heat shield block, in particular for lining a combustion chamber wall, having a hot side which can be subjected to a hot medium, a wall side opposite the hot side, and a peripheral side adjoining the hot side and the wall side. A tension element which can be prestressed to a prestress (Fz) is attached to the peripheral side, release of a fragment, formed during a fracture, of the heat shield block being reliably prevented by the prestress (Fz) of the tension element. The invention also relates to the use of a heat shield block, in particular for lining a combustion chamber wall of a gas turbine.

Abstract: A vane assembly for a turbine assembly includes an inner endcap, an outer endcap, and a body. The body includes a metallic core assembly, a ceramic shell assembly and a support assembly. The metallic core assembly is coupled to the inner and outer endcaps and bears most of the mechanical loads, including aerodynamic loads. The ceramic shell bears substantially all of the thermal stress placed on the vane assembly. The support assembly is disposed between the metallic core assembly and said ceramic shell assembly and is coupled to the metallic core assembly.