Abstract: A coated product having coating that includes a layer of hard material having a defined multi-ply layer structure, thereby significantly minimizing or preventing heat input into the coated substrate resulting from the effect of thermal hot spots.

Abstract: A hard material layer system with a multilayer structure, comprising alternating layers A and B, with A layers having the composition MeApAOnANmA in atomic percent and B layers having the composition MeBpBOnBNmB in atomic percent, where the thermal conductivity of the A layers is greater than the thermal conductivity of the B layers. MeA and MeB each comprise at least one metal of the group Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, and Al, pA indicates the atomic percentage of MeA and pB indicates the atomic percentage of MeB and the following is true: PA=PB, nA indicates the oxygen concentration in the A layers in atomic percent and nB indicates the oxygen concentration in the B layers in atomic percent and the following is true: nA<nB, and mA indicates the nitrogen concentration in the A layers in atomic percent and mB indicates the nitrogen concentration in the B layers in atomic percent and the following is true: pA/(nA+mA)=pB/(nB+mB).

Abstract: A coated product having coating that includes a layer of hard material having a defined multi-ply layer structure, thereby significantly minimizing or preventing heat input into the coated substrate resulting from the effect of thermal hot spots.

Abstract: A hard material layer system with a multilayer structure, comprising alternating layers A and B, with A layers having the composition MeApAOANmA in atomic percent and B layers having the composition MeBpBOnBNmB in atomic percent, where the thermal conductivity of the A layers is greater than the thermal conductivity of the B layers. MeA and MeB each comprise at least one metal of the group Ti, Zr, Hf, V, Nb, Ta, Cr, Mo, W, and Al, pA indicates the atomic percentage of MeA and pB indicates the atomic percentage of MeB and the following is true: PA=PB, nA indicates the oxygen concentration in the A layers in atomic percent and nB indicates the oxygen concentration in the B layers in atomic percent and the following is true: nA<nB, and mA indicates the nitrogen concentration in the A layers in atomic percent and mB indicates the nitrogen concentration in the B layers in atomic percent and the following is true: pA/(nA+mA)=pB/(nB+mB).

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: An optical sensor device for local analysis of a combustion process in a combustor of a thermal power plant, in particular a gas turbine plant, includes at least one wavelength selective optical element exposed directly or indirectly to hot combustion gases being produced by said combustion process, the optical element including an array of nano- and/or microcrystalline fibres which are created by shear flow crystallization.

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: An optical sensor device for local analysis of a combustion process in a combustor of a thermal power plant, in particular a gas turbine plant, includes at least one wavelength selective optical element exposed directly or indirectly to hot combustion gases being produced by said combustion process, the optical element including an array of nano- and/or microcrystalline fibres which are created by shear flow crystallization.

Abstract: Multinary alloys, in particular for use as coatings, if appropriate in combination with other types of layers, for components which are exposed to high temperatures and corrosive gases. The alloys are of the general form: Al—Ni—Ru-M, where at least one B2 phase is present, the aluminum content being in the range from 26–60 atomic percent and where M may be one or more metals and/or semimetals selected from the group consisting of: precious metal, transition metal, rare earths, semimetal. Multinary alloys of this type are very stable with respect to oxidation, have a low thermal conductivity and in particular have similar coefficients of thermal expansion to superalloys, which are usually used as substrates for protective coatings of this type in gas turbine components.

Abstract: The present invention relates to an icosahedral, quasicrystalline compound or compound present in the form of an approximant having the nominal composition: TivCrwAlxSiyOz, in which v=60-65; w=25-30; x=0-6; Y=8-15; z=8-20; and in which the atom percent of oxygen is in the range of between 8 and 15%, and that of aluminum in the range of between 2 to 5%. Due to their layered structure and ceramic intermediate layers, compounds of this type exhibit excellent properties, in particular for use as coatings for gas turbine components, such as for example, rotor blades or guide vanes.

Abstract: Multinary alloys, in particular for use as coatings, if appropriate in combination with other types of layers, for components which are exposed to high temperatures and corrosive gases. The alloys are of the general form: Al—Ni—Ru-M, where at least one B2 phase is present, the aluminum content being in the range from 26-60 atomic percent and where M may be one or more metals and/or semimetals selected from the group consisting of: precious metal, transition metal, rare earths, semimetal. Multinary alloys of this type are very stable with respect to oxidation, have a low thermal conductivity and in particular have similar coefficients of thermal expansion to superalloys, which are usually used as substrates for protective coatings of this type in gas turbine components.

Abstract: The present invention relates to an icosahedral, quasicrystalline compound or compound present in the form of an approximant having the nominal composition: TivCrwAlxSiyOz, in which v=60-65; w=25-30; x=0-6; Y=8-15; z=8-20; and in which the atom percent of oxygen is in the range of between 8 and 15%, and that of aluminum in the range of between 2 to 5%. Due to their layered structure and ceramic intermediate layers, compounds of this type exhibit excellent properties, in particular for use as coatings for gas turbine components, such as for example, rotor blades or guide vanes.