Abstract:
A stator component of a turbomachine is composed substantially of at least one axially extending outer ring (10) which serves as a frame of an inner ring composed of partial segments (20). The partial segments are arranged on one another such that, on the rotor side, they form a coherent circular circumferential surface in relation to the rotational movement of rotor blades (30). The individual partial segment (20) is composed of a material of uniform construction or, at least in a radial direction, of multiple partial bodies constructed from different materials, such as for example ceramic, wherein a partial segment thus formed exhibits predetermined stress and/or expansion behaviour as a function of the load ranges of the turbomachine.
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:
The invention relates to a method for manufacturing a metal-ceramic composite structure intended to be exposed to high temperatures. The composite structure includes a base metal structure or component, which is on at least one side covered and permanently joined with one or more ceramic tiles.
Abstract:
A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).
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:
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.