Abstract: The invention relates to an anodic bonding method for bonding two elements with an intermediate layer. The invention especially, but not exclusively, relates to an anodic bonding method for between a metallic element and a heterogeneous element, for example a glass, artificial sapphire or ceramic element. The specificity and aim of the present invention is to produce an assembly that is gas-tight and fluid-tight, solderless, brazing- or welder-free and without organic compound (glue). The present method has multiple industrial applications, including making it possible to attach a watch-glass, typically made of mineral glass, sapphire or transparent or translucent ceramics, to a bezel or case middle of a watch case using the anodic bonding technique.

Abstract: The invention relates to an anodic bonding method for bonding two elements with an intermediate layer. The invention especially, but not exclusively, relates to an anodic bonding method for between a metallic element and a heterogeneous element, for example a glass, artificial sapphire or ceramic element. The specificity and aim of the present invention is to produce an assembly that is gas-tight and fluid-tight, solderless, brazing- or welder-free and without organic compound (glue). The present method has multiple industrial applications, including making it possible to attach a watch-glass, typically made of mineral glass, sapphire or transparent or translucent ceramics, to a bezel or case middle of a watch case using the anodic bonding technique.

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: The invention refers to a method for producing means with thermal resist for applying at a surface of a heat exposed component. The method includes providing at least one mixture of at least two different inorganic powder materials: with different chemical composition and thermal expansion coefficient, where at least one of the powder materials experiences volume changes due to crystallographic phase change at a given temperature, and/or\ where at least one of the two powder materials experiences volume changes due to chemical composition change, forming the at least one mixture into a green body shape, sintering the green body to obtain a ceramic body and cooling the ceramic body and causing micro-cracking during heating and or/sintering and/or cooling to obtain the means with thermal resist. The forming is performed such that a first mixture forming a first layer onto which a second mixture is applied forming a second layer differs in porosity from that first layer to obtain a layered green body.

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 refers to a method for applying heat resistant protection components onto the surface of a heat exposed component. The method including providing at least two separate heat protection components, and joining the at least two separate heat protection components onto their top surface and/or bottom surface and/or at least one side surface by flexible means for obtaining an integrally handable entity. The method further includes fixing the integrally handable entity by applying and brazing the surface of each heat protection component on the surface of the heat exposed component. The materials of the flexible means and for joining the flexible means on the separate heat protection components are selected such that the materials withstand brazing being performed under protective atmosphere, i.e. an atmosphere without or with reduced amount of oxygen, at process temperatures between 700° C. and 1200° C., and that the materials are burned out after brazing during a following oxidizing thermal step.

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: The invention refers to a method for applying heat resistant protection components onto the surface of a heat exposed component. The method including providing at least two separate heat protection components, and joining the at least two separate heat protection components onto their top surface and/or bottom surface and/or at least one side surface by flexible means for obtaining an integrally handable entity. The method further includes fixing the integrally handable entity by applying and brazing the surface of each heat protection component on the surface of the heat exposed component. The materials of the flexible means and for joining the flexible means on the separate heat protection components are selected such that the materials withstand brazing being performed under protective atmosphere, i.e. an atmosphere without or with reduced amount of oxygen, at process temperatures between 700° C. and 1200° C., and that the materials are burned out after brazing during a following oxidizing thermal step.

Abstract: The invention refers to a method for producing means with thermal resist for applying at a surface of a heat exposed component. The method includes providing at least one mixture of at least two different inorganic powder materials: with different chemical composition and thermal expansion coefficient, where at least one of the powder materials experiences volume changes due to crystallographic phase change at a given temperature, and/or\where at least one of the two powder materials experiences volume changes due to chemical composition change, forming the at least one mixture into a green body shape, sintering the green body to obtain a ceramic body and cooling the ceramic body and causing micro-cracking during heating and or/sintering and/or cooling to obtain the means with thermal resist. The forming is performed such that a first mixture forming a first layer onto which a second mixture is applied forming a second layer differs in porosity from that first layer to obtain a layered green body.

Abstract: The invention refers to a method for fixing a heat resistant component on a surface of a heat exposed component, by brazing of at least a part of a surface of the heat resistant component limited by a peripheral boundary edge on the surface of the heat exposed component using a molten solder. A first alternative includes: metallizing the surface of the heat resistant component at least with the exception of an edge area comprising the peripheral boundary edge; and brazing said metallized surface to the surface of the heat exposed component, wherein at least the surface of the heat resistant component consists of a ceramic material which has a physico-chemical property concerning wettability such that the ceramic material is not wettable by the molten solder, and/or a metal or a metal alloy is used for metallizing which has a physico-chemical property concerning wettability such that the metallizing is wettable by the molten solder.

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.