Abstract: The invention relates to an abrasive material including a nickel aluminide intermetallic phase, in particular a beta nickel aluminide (?-NiAl) intermetallic phase with a Laves phase, as a matrix for abrasive particles. It also relates to a method manufacturing an abrasive material and a blade in a turbomachinery with an abrasive material.

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 bearing element for at least one adjustable guide vane of a turbomachine, in particular an aircraft engine, is provided. The bearing element comprising a porous matrix made of carbon and/or graphite and at least one metallic phase or a metal salt that is at least partially arranged inside the pores of the matrix, so that what results is a metal-infiltrated or a metal-salt-infiltrated material.

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 coating a substrate having a cavity structure, in particular a cooling structure, inside the substrate, wherein the cavity structure includes openings in the surface of the substrate. At least one bonding layer, in particular a diffusion layer, or at least one metallic layer is applied onto the substrate, in particular onto the surface of the substrate, and subsequently at least one thermal protection layer is applied onto the at least one diffusion layer by using a plasma spray physical vapour deposition (PS-PVD) method, a hollow cathode sputtering method or a suspension plasma spray (SPS) method.

Abstract: A bearing element for at least one adjustable guide vane of a turbomachine, in particular an aircraft engine, is provided. The bearing element comprising a porous matrix made of carbon and/or graphite and at least one metallic phase or a metal salt that is at least partially arranged inside the pores of the matrix, so that what results is a metal-infiltrated or a metal-salt-infiltrated material.

Abstract: A holding device for a substrate during the performance of a generative laser method for applying a coating that comprises hard substance particles to a top surface of the substrate is provided. The wall of the substrate is completely surrounded by a thermoconductive wall of the holding device at least in the area of the top side. The wall of the holding device protrudes beyond the top side with a projection that is at least in the size range of the thickness of the coating and the wall of the holding device is arranged perpendicular to the top side, so that a laser-induced molten coating bath can be supported by means of the wall of the holding device, and the coating has the shape of the substrate in the horizontal cross-section.

Abstract: A method for manufacturing a thermally deformable component for high thermal loads, includes: providing a first area of the component with a first metallic material by a generative laser process, or making the first area of the first metallic material; providing a second area of the component with a second metallic material by a generative laser process, or making the second area of the second metallic material; where at least one of the metallic materials is deposited by the generative laser process, and a ratio of a linear expansion coefficient ?1 of the first metallic material and of a linear expansion coefficient ?2 of the second metallic material is as: ? 2 ? ( T 2 ) ? 1 ? ( T 1 ) = x ? ? T 1 - T 0 ? ? T 2 - T 0 ? , where x=0.5 to 1; T1=mean operating temperature on a hot side; T0=reference temperature; T2=mean operating temperature on a cold side.