Abstract: The invention relates to a steam turbine rotor wherein the inter blade region rotor surface, the feed region rotor surface, the piston region rotor surface and the stress relief groove rotor surface of the rotor are configured and arranged as steam exposed surfaces during normal operation of the steam turbine rotor. The steam turbine rotor has a thermal barrier coating on at least the piston region rotor surface.

Abstract: The invention relates to a steam turbine rotor wherein the inter blade region rotor surface, the feed region rotor surface, the piston region rotor surface and the stress relief groove rotor surface of the rotor are configured and arranged as steam exposed surfaces during normal operation of the steam turbine rotor. The steam turbine rotor has a thermal barrier coating on at least the piston region rotor surface.

Abstract: The invention relates to a steam turbine rotor wherein the inter blade region rotor surface, the feed region rotor surface, the piston region rotor surface and the stress relief groove rotor surface of the rotor are configured and arranged as steam exposed surfaces during normal operation of the steam turbine rotor. The steam turbine rotor has a thermal barrier coating on at least the piston region rotor surface.

Abstract: A composite turbine blade for high-temperature applications such as gas turbines or the like includes a root for mounting the blade in a corresponding circumferential assembly groove of a rotor and an airfoil connected to said root. An inner carrying structure is provided extending at least over a portion of the root as well as at least a portion of said airfoil. The inner carrying structure is made of a high strength eutectic ceramic and the airfoil is made of a ceramic matrix composite (CMC) material.

Abstract: A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration.

Abstract: A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration.

Abstract: Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions extending from the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.

Abstract: The invention relates to a steam turbine rotor wherein the inter blade region rotor surface, the feed region rotor surface, the piston region rotor surface and the stress relief groove rotor surface of the rotor are configured and arranged as steam exposed surfaces during normal operation of the steam turbine rotor. The steam turbine rotor has a thermal barrier coating on at least the piston region rotor surface.

Abstract: A composite turbine blade for high-temperature applications such as gas turbines or the like includes a root for mounting the blade in a corresponding circumferential assembly groove of a rotor and an airfoil connected to said root. An inner carrying structure is provided extending at least over a portion of the root as well as at least a portion of said airfoil. The inner carrying structure is made of a high strength eutectic ceramic and the airfoil is made of a ceramic matrix composite (CMC) material.

Abstract: A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration.

Abstract: Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions located in the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.

Abstract: A high temperature thermal barrier coating which consists of a stabilized ZrO2 composition for the protection of thermally loaded components (10, 10?) of a thermal machine, especially a gas turbine, is disclosed. The thermal barrier coating is stabilized with at least 15 mol % Y1+v Ta1?vO4?v, the ZrO2 is partially substituted by at least 10 mol % HfO2 and the composition is established according to the formula (Y1+vTa1?vO4?v)z(Zr1?xHfxO2)1?z, with x ranging from 0.1 to 0.5, v ranging from ?0.1 to 0.2 and z ranging from 0.15 to 0.25.

Abstract: Components (1) have a thermal barrier coating (2-6) on the surface thereof, wherein the thermal barrier coating includes at least one layer (3) having chemically stabilized zirconia, and wherein at least indirectly adjacent to the layer (3) with chemically stabilized zirconia and on its surface facing side, there is provided a protective layer (4) and/or a infiltration zone (5) which does not react with environmental contaminant compositions that contain oxides of calcium and which does not react with the material of the layer (3) having chemically stabilized zirconia. Methods for making such components as well as to uses of specific systems for coating thermal barrier coatings, can prevent CMAS.

Abstract: Components (1) have a thermal barrier coating (2-6) on the surface thereof, wherein the thermal barrier coating includes at least one layer (3) having chemically stabilized zirconia, and wherein at least indirectly adjacent to the layer (3) with chemically stabilized zirconia and on its surface facing side, there is provided a protective layer (4) and/or a infiltration zone (5) which does not react with environmental contaminant compositions that contain oxides of calcium and which does not react with the material of the layer (3) having chemically stabilized zirconia. Methods for making such components as well as to uses of specific systems for coating thermal barrier coatings, can prevent CMAS.