Abstract: A method for machining a material, in particular steel, is provided. The material is milled at such a high cutting speed that residual tensile stresses close the surface that exceed a specified value can occur and the residual tensile stresses can be lowered below the specified value by subsequent brushing. A device for performing the method is also provided.

Abstract: A method for machining a material, in particular steel, is provided. The material is milled at such a high cutting speed that residual tensile stresses close the surface that exceed a specified value can occur and the residual tensile stresses can be lowered below the specified value by subsequent brushing. A device for performing the method is also provided.

Abstract: A gas turbine system includes a compressor; a combustion chamber; a gas turbine; and an evaporative cooler. The evaporative cooler includes a plurality of cooling elements, a flow channel, and a feed device. The plurality of cooling elements are arranged in the flow channel. The feed device supplies a liquid to the plurality of cooling elements. The liquid is evaporated or vaporized. Each of the plurality of cooling elements is a flat cooling sheet, a surface of the cooling sheet having hydrophilic properties at least in a subregion which is specified for forming a liquid film. The evaporative cooler is connected ahead of the compressor on an intake side.

Abstract: A turbine blade or vane is provided. The turbine blade or vane includes an airfoil portion, a root portion arranged below the airfoil portion, a dove tail shaped securing portion arranged below the root portion have a surface including subregions that have locally different compressive residual stresses, and a convexly curved sub region arranged on the surface and adjacent to the concavely curved sub region. The concavely curved region has higher compressive residual stresses than the convexly curved region, and the level of the compressive residual stress in the concavely curved region is at least 30% of the component base material yield strength.

Abstract: A turbine blade or vane is provided. The turbine blade or vane includes an airfoil portion, a root portion arranged below the airfoil portion, a dove tail shaped securing portion arranged below the root portion have a surface including subregions that have locally different compressive residual stresses, and a convexly curved sub region arranged on the surface and adjacent to the concavely curved sub region. The concavely curved region has higher compressive residual stresses than the convexly curved region, and the level of the compressive residual stress in the concavely curved region is at least 30% of the component base material yield strength.

Abstract: An evaporative cooler for cooling a gas stream, in particular an air stream, including a number of cooling elements located in a flow channel, is provided. A liquid, preferably water, is supplied by a feed device and will be vaporized or evaporated. In one aspect, the surface of at least one of the cooling elements has hydrophilic properties, at least in one sub-region designed to form a liquid film.

Abstract: The inventive method discloses the local, adapted and controlled introduction of internal compressive stress in convex and concave regions, such as the root region of turbine blades, by means of at least two pressure generators.

Abstract: The inventive method discloses the local, adapted and controlled introduction of internal compressive stress in convex and concave regions, such as the root region of turbine blades, by means of at least two pressure generators.