Abstract: The disclosure relates to a method for operating a gas turbine at a high temperature and to a gas turbine assembly. In the method, a gas turbine having a structural material and a thermal barrier layer disposed on the structural material is cooled down in a decelerated manner after operation at an operating temperature above 1000° C., so that damage to the structural material and/or the thermal barrier layer is minimized. In this way, the gas turbine can be operated permanently at temperatures above 1500° C.

Abstract: A construction element, particularly adapted and configured for use in a turbo engine, in particular an aircraft engine, wherein a bond coat having a bond structure and thereabove a ceramic coat are disposed on a base. The lateral faces of the bond structure in the cross section are configured so as to be free of undercuts, wherein peak structures and/or trough structures are present, and the peak of the cross section of a peak structure has a mean peak angle (?) of less than or equal to 90°, most particularly less than 45°, and/or the trough structure has a valley angle in the range 90°??<170°.

Abstract: A method for generating a structured surface on a substrate includes analyzing a substrate surface of the substrate and selecting, as a function of a condition of the substrate surface, method parameters including focus diameter, pulse peak power, pulse energy, point spacing, pulse length, pulse spacing and/or pulse sequence. The method further includes generating, by partial ablation and partial deposition via treatment with an intensive pulsed laser beam, surface structures having dimensions in the sub-micrometer range such that a multi-scale surface structure in the sub-micrometer and micrometer range adapted to intrinsically inhomogeneous properties of the substrate surface in the sub-micrometer range is generated. The substrate is an inhomogeneous substrate.

Abstract: A method for generating a structured surface on a substrate includes analyzing a substrate surface of the substrate and selecting, as a function of a condition of the substrate surface, method parameters including focus diameter, pulse peak power, pulse energy, point spacing, pulse length, pulse spacing and/or pulse sequence. The method further includes generating, by partial ablation and partial deposition via treatment with an intensive pulsed laser beam, surface structures having dimensions in the sub-micrometer range such that a multi-scale surface structure in the sub-micrometer and micrometer range adapted to intrinsically inhomogeneous properties of the substrate surface in the sub-micrometer range is generated. The substrate is an inhomogeneous substrate.

Abstract: A construction element, particularly adapted and configured for use in a turbo engine, in particular an aircraft engine, wherein a bond coat having a bond structure and thereabove a ceramic coat are disposed on a base. The lateral faces of the bond structure in the cross section are configured so as to be free of undercuts, wherein peak structures and/or trough structures are present, and the peak of the cross section of a peak structure has a mean peak angle (?) of less than or equal to 90°, most particularly less than 45°, and/or the trough structure has a valley angle in the range 90°??<170°.