Abstract: A method for applying a coating 1 to a surface 2 of a mullite material 3 is specified, which comprises pretreating the surface 2 of the mullite material 3 by means of a plasma-chemical process in which molecular hydrogen is excited in such a way that plasma-activated hydrogen is produced S1, and applying an aluminum oxide-containing layer 4 by means of a PVD process to the pretreated surface 2 of the mullite material 3 S2. Furthermore, a mullite material 3 with a coating and a gas turbine component with such a mullite material 3 are specified.

Abstract: Provided is a method for arranging a protective coating for a thermally stressed structure, having at least one layer of alpha-aluminium oxide or of element-modified alpha-aluminium oxide, and wherein the protective coating is applied by reactive cathodic arc vaporization. A protective coating produced by the method and a component having a protective coating is also provided.

Abstract: A method for applying a coating 1 to a surface 2 of a mullite material 3 is specified, which comprises pretreating the surface 2 of the mullite material 3 by means of a plasma-chemical process in which molecular hydrogen is excited in such a way that plasma-activated hydrogen is produced S1, and applying an aluminum oxide-containing layer 4 by means of a PVD process to the pretreated surface 2 of the mullite material 3 S2. Furthermore, a mullite material 3 with a coating and a gas turbine component with such a mullite material 3 are specified.

Abstract: An improved ceramic heat shield for a gas turbine is provided. The ceramic heat shield has a porous ceramic body and according to the embodiments an infiltration coating that is provided in a surface layer of the porous ceramic body and contains an infiltration coating material designed to gas-tightly seal pores of the ceramic body.

Abstract: A ceramic material which contains yttrium oxide as stabilizers and at least one of the materials erbium oxide or ytterbium oxide provides a phase having sintering stability for a ceramic material for ceramic layers and a ceramic layer system which maintain the mechanical and thermal properties for a long time even when used at high temperatures.

Abstract: A ceramic material, in particular for use in a layer system, which has high resistance to sintering, high expansion tolerance and low thermal conductivity and is provided by deliberately choosing the additions of oxides to zirconium oxide.

Abstract: A component including a metallic substrate and a two layered bondcoat is provided. On the substrate a metallic bond coat especially of the type MCrAlY is preferably applied. The bond coat is a two layered metallic layer. The outer metallic bond coat has compared to the inner metallic coat a reduced amount of aluminum and/or chromium.

Abstract: Known protective layers having a high Cr-content and a silicone in addition, form brittle phases that embrittle further under the influence of carbon during use. The protective layer according to the invention is composed of 22% to 26% cobalt (Co), 10.5% to 12% aluminum (Al), 0.2% to 0.4% Yttrium (Y) and/or at least one equivalent metal from the group comprising Scandium and the rare earth elements, 15% to 16% chrome (Cr), optionally 0.3% to 1.5% tantal, the remainder nickel (Ni).

Abstract: Known protective layers having a high Cr content and additionally a silicon form brittle phases which additionally become brittle under the influence of carbon during use. The protective layer hereof has a composition 22% to 24% cobalt (Co), 10.5% to 11.5% aluminum (AI), 0.2% to 0.4% yttrium (Y) and/or at least one equivalent metal from the group comprising scandium and the rare earth elements, 14% to 16% chrome (Cr), optionally 0.3% to 0.9% tantalum, the remainder nickel (Ni).

Abstract: Provided is a method for arranging a protective coating for a thermally stressed structure, having at least one layer of alpha-aluminium oxide or of element-modified alpha-aluminium oxide, and wherein the protective coating is applied by reactive cathodic arc vaporization. A protective coating produced by the method and a component having a protective coating is also provided.

Abstract: A ceramic material including at least erbium oxide (Er2O3)-stabilized zirconium oxide (ZrO2). The erbium oxide-stabilized zirconium oxide can be used as ceramic thermal barrier layer. Crack resistance of such ceramic materials is considerably increased by using erbium oxide-stabilized zirconium oxide.

Abstract: The use of different ceramic layers allows different configurations of gas turbines to be produced each of which is optimized for a respective use of base load operation or peak load operation.

Abstract: A ceramic material which contains yttrium oxide as the stabilizer and at least one of the materials erbium oxide or ytterbium oxide provides a phase having sintering stability for a ceramic material for ceramic layers and a ceramic layer system which maintain the mechanical and thermal properties for a long time even when used at high temperatures.

Abstract: A ceramic material is provided by deliberately choosing the additions of oxides to form zirconium oxide, in particular for the use of a layer system which has a high resistance to sintering, high expansion tolerance and low thermal conductivity.

Abstract: An improved ceramic heat shield for a gas turbine is provided. The ceramic heat shield has a porous ceramic body and according to the embodiments an infiltration coating that is provided in a surface layer of the porous ceramic body and contains an infiltration coating material designed to gas-tightly seal pores of the ceramic body.

Abstract: Through the use of different ceramic heat insulation coatings (7, 13) on turbine blades, it is possible to produce or restore different configurations of gas turbines, which are then optimized for a respective baseload operation application or peak load operation application. Differences in the sprayed-on heat insulation coatings (7, 13) can be generated by means of a different material composition of the powder, for example zirconium oxide, by means of a different number of layers (10), by means of different coating thicknesses and/or by means of different porosities.

Abstract: A metallic bond coat Ni16+/?1% Co15+/?1% Cr 8+/?0.5% Al2+/?0.2% Ta0.5+/?0.1% Y: Sicoat 2496 leads to a fusion barrier of titanium into the metallic bond coat so that a substrate is not depleted by titanium.

Abstract: The use of different ceramic layers allows different configurations of gas turbines to be produced each of which is optimized for a respective use of base load operation or peak load operation.

Abstract: The use of different ceramic layers allows different configurations of gas turbines to be produced each of which is optimized for a respective use of base load operation or peak load operation.

Abstract: Provided is a special type of corrosion protection for ceramic thermal insulation layers which is produced by joining hollow aluminum oxide particles and an outer glass layer, which is produced; in particular, by thermal treatment.