Abstract: Compressor rotor structure and methodology for harmonizing compressor aerodynamics and rotordynamics are provided. Disclosed embodiments benefit from a compressor design effective for improving rotordynamics (e.g., stiffer rotor structure) without reducing a usable aerodynamics range of the compressor. This design may involve variation of the rotor structure along the rotor axis to locate respective surfaces defined by respective inlets of the one or more impellers at a varying distance relative to the rotor axis based on respective ratios selected for the configuration of the impeller bodies. This arrangement may be effective for improving rotordynamics while satisfactorily meeting the respective varying aerodynamics requirements at the various compression stages by the impeller bodies.

Abstract: The invention relates to a method for production of turbine components having at least one flow body, which has cooling air outlet openings arranged in the area of its trailing edge with the flow body, for example a blade section, being provided with an in particular ceramic coating by spraying coating. According to the invention, before the coating is applied, the cooling air outlet openings are completely covered by a covering strip which is composed of a material which is resistant to the coating process.

Abstract: The invention relates to a method of preparing turbine blades for spray coating their blade region that is subjected to the medium flowing through during operation in a spray coating apparatus, in which the turbine blade is inserted with its blade root into a cavity of a mounting in such a way that it protrudes with the blade region that adjoins the blade root from an opening of the cavity to form a gap between the rim of the opening and the turbine blade, and in which the gap is bridged by a shielding fixed on the mounting, which is characterized in that a shielding layer of a plastic which is resistant during the spray coating is used for the shielding, the shielding layer being arranged in such a way that it reaches up to the boundary between the blade root and the blade region.

Abstract: A method is provided for coating a component with a multilayer ceramic coating in which the individual layers of the ceramic coating are applied covering one another on the component, and in which ceramic particles are supplied to a coating burner, melted partly or completely by the coating burner, and deposited on the component. The ceramic particles have a particle size, which increases from layer to layer, and are supplied to the coating burner. Furthermore, a multilayer ceramic coating and a component which has with a multilayer ceramic coating are provided.

Abstract: The invention relates to a method of preparing turbine blades for spray coating their blade region that is subjected to the medium flowing through during operation in a spray coating apparatus, in which the turbine blade is inserted with its blade root into a cavity of a mounting in such a way that it protrudes with the blade region that adjoins the blade root from an opening of the cavity to form a gap between the rim of the opening and the turbine blade, and in which the gap is bridged by a shielding fixed on the mounting, which is characterized in that a shielding layer of a plastic which is resistant during the spray coating is used for the shielding, the shielding layer being arranged in such a way that it reaches up to the boundary between the blade root and the blade region.