Abstract: A layer system including a substrate on which a first layer is positioned is provided. The first layer includes a thermographic material. The thermographic material is a pyrochlore phase doped with at least one rare earth material. The rare earth material is selected from the group europium, terbium, erbium, dysprosium, samarium, holmium, praseodymium, ytterbium, neodymium, and thulium. A method of a layer system is also provided.

Abstract: A thermal barrier coating including a two layered ceramic barrier coating, an inner ceramic layer and an outer ceramic layer, is provided. The thermal barrier coating has different thicknesses on different places of the component. In addition, the thickness of the inner ceramic layer and the thickness of the outer ceramic layer vary in relation to one another.

Abstract: In addition to good thermal barrier properties, thermal barrier coating systems also have to have a long thermal barrier coating service life. The coating system according to the invention comprises a specially adapted layer sequence made up of metallic bonding layer, which consists of an NiCoCrAlX, inner ceramic layer and outer ceramic layer, at least 80% of which is made up of the pyrochlore phase Gd2Zr2O7 or Gd2Hf2O7.

Abstract: The invention relates to a method for inspecting especially a gas turbine installation or steam turbine installation. According to said method, an actual condition of a component of the turbine installation is determined using a suitable system, the determined actual condition is compared with a predetermined desired condition of the component, and the result of comparison between the actual condition and the desired condition is used to determine whether an overall inspection of the turbine installation is required. The component is a guide vane whose angular position in relation to the direction of influx is the actual condition to be determined. The actual condition is determined by means of an imaging device. The invention also relates to a turbine inspection system for carrying out the method.

Abstract: Thermal barrier coating layer systems, in addition to good thermal barrier properties, also have to have a long service life of the thermal barrier coating. The layer system according to the invention comprises a specially adapted layer sequence of metallic bonding layer, inner ceramic layer and outer ceramic layer.

Abstract: Thermal barrier coating layer systems, in addition to good thermal barrier properties, also have to have a long service life of the thermal barrier coating. The layer system according to the invention comprises a specially adapted layer sequence of metallic bonding layer, inner ceramic layer and outer ceramic layer.

Abstract: Method for recording microstructural changes in a layer system component. A specific material parameter of the component is measured. The layer system may include an alloy substrate and an alloy or porous ceramic layer. The material parameter may be measured a plurality of times. The measured material parameter may include electrical capacitance, specific heat capacity, peltier coefficient or magnetic susceptibility. The material parameter may first be measured on a new component and subsequent measurements may be performed at a time interval after operational use. The recorded material parameter is then used to determine microstructural changes in the substrate or the layer material of the component caused by changes in precipitation, cracks, or depletion of an alloying element.

Abstract: Heat insulating layered systems should have a long service life in addition to excellent heat-insulating properties. Disclosed in an inventive layered system consisting of an external ceramic layer that has a mixed crystal consisting of gadolinium zirconate and gadolinium hafnate.

Abstract: Heat-insulating layer systems have to be provided with along service life of the heat-insulating layer in addition to having good heat-insulating properties. The inventive layer system comprises a ceramic layer which contains a mixture of two pyrochlore phases.

Abstract: The invention relates to a coating system (2) for a component (1) which comprises a porous layer (3) and an abradable layer (4) on the porous layer (3). Further the invention relates to an assembly of two components (1) which are relatively movable to each other and form a gap in between. One component (1) is provided with a coating system (2) and the other component (1) is in sliding contact with the coating system (2).

Abstract: The invention relates to a method for repairing components comprising a base material with an oriented microstructure, wherein the repair point comprises a correspondingly oriented microstructure as the surrounding base material. According to the inventive method, solder is applied in the region of a point which is to be repaired and is soldered to the component by means of a heating effect produced by a device. A temperature gradient, i.e., approximately a temperature characteristic, is produced during the heating effect, said temperature characteristic ranging from a high to a low temperature in the region of the point which is to be repaired.

Abstract: The microstructure of components, particularly layer systems, deteriorates under excessive thermal and/or mechanical stress. Previous test methods are destructive, parts being cut out of the layer system and being microstructurally analyzed. The inventive method allows a deterioration to be determined by means of special, simple non-destructive measurements that are repeated at specific intervals using a mechanical indenter test, for example.

Abstract: Thermal barrier coating layer systems, in addition to good thermal barrier properties, also have to have a long service life of the thermal barrier coating. The layer system according to the invention comprises a specially adapted layer sequence of metallic bonding layer inner ceramic layer and outer ceramic layer.

Abstract: Disclosed is a gas turbine blade (1) having a ceramic heat-insulating layer (17). The ceramic heat-insulating layer (17) consists of 10-95% wt. % magnesium aluminate, 5-90 wt. % magnesium oxide and 0-20 wt. % aluminum oxide. Magnesium oxide particles are incorporated into a matrix made of spindle-shaped magnesium aluminate, enabling the thermal expansion coefficient of the ceramic heat-insulating layer (17) to be adapted in a particularly suitable manner to a metallic base body (15) of the gas turbine blade (1). The ceramic heat-insulating layer (17) also has a porosity which is greater that 3 vol. %, thereby guaranteeing sufficiently low heat conductivity.

Abstract: Disclosed is a gas turbine blade (1) having a ceramic heat-insulating layer (17). The ceramic heat-insulating layer (17) consists of 10-95% wt. % magnesium aluminate, 5-90 wt. % magnesium oxide and 0-20 wt. % aluminum oxide. Magnesium oxide particles are incorporated into a matrix made of spindle-shaped magnesium aluminate, enabling the thermal expansion coefficient of the ceramic heat-insulating layer (17) to be adapted in a particularly suitable manner to a metallic base body (15) of the gas turbine blade (1). The ceramic heat-insulating layer (17) also has a porosity which is greater that 3 vol. %, thereby guaranteeing sufficiently low heat conductivity.