Abstract: A device for recontouring a gas turbine blade includes: a holding device having at least one cutting tool; and a guide configured to guide the cutting tool along a leading edge of the gas turbine blade. The cutting tool is configured to remove material from the gas turbine blade using a rotational movement about an axis of rotation. The axis of rotation forms an angle together with a chord of the gas turbine blade in a profile section plane, which extends perpendicularly to a radial extent of the gas turbine blade, and the angle is less than 45°.

Abstract: A flow element for fluidic contact with a hot gas flow inside an aircraft engine includes: a base material, which has a hot gas surface that faces the gas flow and a remote surface that is remote from the gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface; an adhesive layer on the chroming layer in first portions; an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and a thermal barrier layer being arranged on the alitising layer in the first portions. The alitising layer is arranged on the chroming layer in second portions that do not have an adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions.

Abstract: A flow element for fluidic contact with a hot gas flow inside an aircraft engine includes: a base material, which has a hot gas surface that faces the gas flow and a remote surface that is remote from the gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface; an adhesive layer on the chroming layer in first portions; an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and a thermal barrier layer being arranged on the alitising layer in the first portions. The alitising layer is arranged on the chroming layer in second portions that do not have an adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions.

Abstract: A device for recontouring a gas turbine blade includes: a holding device having at least one cutting tool; and a guide configured to guide the cutting tool along a leading edge of the gas turbine blade. The cutting tool is configured to remove material from the gas turbine blade using a rotational movement about an axis of rotation. The axis of rotation forms an angle together with a chord of the gas turbine blade in a profile section plane, which extends perpendicularly to a radial extent of the gas turbine blade, and the angle is less than 45°.

Abstract: A method makes contact with a doping region formed at a substrate surface of a substrate. An insulating layer is applied on the substrate surface and a contact hole is formed in the insulating layer. A metal-containing layer is subsequently deposited on the insulating layer and the surface region of the doping region that is uncovered by the contact hole. In a subsequent thermal process having two steps, first the metal-containing layer is reacted with the silicon of the doping region to form a metal silicide layer and then the rest of the metal-containing layer is converted into a metal-nitride-containing layer in a second thermal step.

Abstract: The novel method allows monitoring of nitrogen processes by making use of the fact that the incorporation of nitrogen near the surface in silicon, or in a thin silicon nitride layer on the silicon surface, inhibits the diffusion of oxygen during the subsequent thermal oxidation. Accordingly, the oxidation rate of the thermal oxidation is reduced and the growth of the oxide layer on the silicon surface is inhibited. The thickness of the oxide layer is thus used as a measure for the nitrogen content, i.e., for the quality of the nitrogen process.

Abstract: The novel method allows monitoring of nitrogen processes by making use of the fact that the incorporation of nitrogen near the surface in silicon, or in a thin silicon nitride layer on the silicon surface, inhibits the diffusion of oxygen during the subsequent thermal oxidation. Accordingly, the oxidation rate of the thermal oxidation is reduced and the growth of the oxide layer on the silicon surface is inhibited. The thickness of the oxide layer is thus used as a measure for the nitrogen content, i.e., for the quality of the nitrogen process.