Abstract: A method for operating a condenser, wherein the condenser is designed for condensing water vapor to form water and during operation a condensate having water accumulates in the condenser, wherein on the condensate surface a plurality of floating bodies are arranged on the condensate, wherein the floating bodies float on the condensate, wherein a large number of floating bodies are used in such a way that the condensate surface is covered, wherein the floating bodies are of spherical and/or sphere-like design, and wherein floating bodies with different sizes are used.

Abstract: A steam turbine system including a steam turbine which has a turbine housing and at least one turbine shaft accommodated in the turbine housing and sealed by seals, a condenser connected fluidically to the steam turbine, an evacuation unit connected fluidically to the condenser, and a dry air source which is connected fluidically to the steam turbine, wherein the steam turbine system is designed in such a way that the evacuation unit is optionally fluidically connectable to the dry air source. A method for preserving components of a steam turbine system to prevent idle-state corrosion is also provided, which the steps: shutting down a steam turbine of the steam turbine system and sucking dry air into the steam turbine using an evacuation unit which additionally functions during intended operation of the steam turbine to exhaust a resulting amount of gas into a condenser.

Abstract: There are a multiplicity of methods of making through-holes. In particular in the production of a multiplicity of film-cooling holes, as in gas turbine blades or combustion chamber elements, small time advantages are also important when making a hole. The method according to the invention, to make the hole close to the final contour in each case in sections in a top and a bottom region in order to then produce the final contour with other laser parameters, achieves time advantages.

Abstract: There are a multiplicity of methods of making through-holes. In particular in the production of a multiplicity of film-cooling holes, as in gas turbine blades or combustion chamber elements, small time advantages are also important when making a hole. The method according to the invention, to make the hole close to the final contour in each case in sections in a top and a bottom region in order to then produce the final contour with other laser parameters, achieves time advantages.

Abstract: There are a multiplicity of methods of making through-holes. In particular in the production of a multiplicity of film-cooling holes, as in gas turbine blades or combustion chamber elements, small time advantages are also important when making a hole. The method according to the invention, to make the hole close to the final contour in each case in sections in a top and a bottom region in order to then produce the final contour with other laser parameters, achieves time advantages.

Abstract: There are a multiplicity of methods of making through-holes. In particular in the production of a multiplicity of film-cooling holes, as in gas turbine blades or combustion chamber elements, small time advantages are also important when making a hole. The method according to the invention, to make the hole close to the final contour in each case in sections in a top and a bottom region in order to then produce the final contour with other laser parameters, achieves time advantages.

Abstract: There are a multiplicity of methods of making through-holes. In particular in the production of a multiplicity of film-cooling holes, as in gas turbine blades or combustion chamber elements, small time advantages are also important when making a hole. The method according to the invention, to make the hole close to the final contour in each case in sections in a top and a bottom region in order to then produce the final contour with other laser parameters, achieves time advantages.

Abstract: Coatings which are applied to a component have to be removed again in a complex way in certain regions, since a coating was not desired to be present in those regions. The subsequent removal of this layer adversely affects the component, for example its geometry. The method according to the invention for coating a component includes a masking which at least partially comprises a ceramic powder and can therefore easily be removed after the component has been coated.

Abstract: Process and apparatus for producing a turbine component, turbine component and use of the apparatus Turbine components have to withstand high thermal and mechanical loads. It therefore proves advantageous for them to be made from a material with a preferred crystal orientation. Hitherto, the turbine components with a preferred crystal orientation have been produced as a single piece, with relatively high scrap rates. The proposed concept makes it possible to produce a preferred turbine component (9, 10) in a particularly simple way by assembling a turbine component (9, 10) at least from a first base part (1) and a build-up material (8), the subregion (7) of the joining zone having a preferred crystal orientation (2), so that disadvantageous properties of a joining zone without a preferred crystal orientation (2) which have hitherto been encountered are avoided.

Abstract: There are a multiplicity of methods of making through-holes. In particular in the production of a multiplicity of film-cooling holes, as in gas turbine blades or combustion chamber elements, small time advantages are also important when making a hole. The method according to the invention, to make the hole close to the final contour in each case in sections in a top and a bottom region in order to then produce the final contour with other laser parameters, achieves time advantages.

Abstract: Methods according to prior art for producing three-dimensional molded bodies generally require outer molds which define the geometry of a component to be produced. The inventive method for producing three-dimensional molded bodies renders one such mold redundant. The geometry of a component to be produced is defined by a pre-determined laser guidance or by the geometry of the partial quantities used.

Abstract: On account of their type of coating, layer systems of the prior art often exhibit poor adhesion to the substrate. If the components are subject to high mechanical stresses, the layer can then become detached. The layer system according to the invention has separately produced anchoring means which allow stronger attachment to the substrate than the attachment of the outer layer to the substrate.

Abstract: Masking layers for components according to the prior art react with the base material of the component and/or are difficult to remove again. The component according to the invention has a masking layer which can very easily be removed following coating of the components, since on the one hand the bonding between the masking layer and the base material of the component is poor, or the masking layer can easily be removed through penetration of a liquid.

Abstract: In the case of the epitaxial growth according to the prior art, a number o strips often have to be produced in a plane in order to restore an area to be repaired. This leads to overlapping and misorientation of the crystalline structures. In the case of the method according to the invention, the strip is of such a width that no overlapping occurs, since the width is adapted to the contour of the area to be repaired.

Abstract: A method for removing a layer area of a component in which the component is firstly treated in at least one salt bath, and then, in a further method step, treated at least once in an acid bath. The method can include adding sodium oxide to a salt bath as an oxygen donor treating the component with a salt bath wherein the salt bath is selected from the group consisting of: sodium hydroxide and potassium hydroxide and treating the component with an acid bath wherein the acid bath is selected from the group consisting of: nitric acid and phosphoric acid.

Abstract: On account of their type of coating, layer systems of the prior art often exhibit poor adhesion to the substrate. If the components are subject to high mechanical stresses, the layer can then become detached. The layer system according to the invention has separately produced anchoring means which allow stronger attachment to the substrate than the attachment of the outer layer to the substrate.

Abstract: On account of their form of coating, layer systems according to the prior art often only have a low level of attachment to the substrate. The layer may then become detached in the event of high mechanical loads being applied to the components. The layer system according to the invention has separately produced anchoring means which are more strongly attached to the substrate than the attachment of the layer to the substrate.

Abstract: Masking layers for components according to the prior art react with the base material of the component and/or are difficult to remove again. The component according to the invention has a masking layer which can very easily be removed following coating of the components, since on the one hand the bonding between the masking layer and the base material of the component is poor, or the masking layer can easily be removed through penetration of a liquid.

Abstract: Prior art methods for removing a layer area of a component (stripping) lead to poor results since a removal, for example, ensues in a nonuniform manner. In addition, these prior art methods are time intensive. An inventive method for removing a layer area of a component consists of firstly treating the layer areas to be removed with a salt solution and then with acid, whereby in an intermediate or final step, the component is treated with a complexing agent.

Abstract: Alloys known in prior art cannot be processed well enough for producing a part. According to the inventive method, the part is subjected to a thermal treatment in an intermediate step, which improves the processability thereof.