Abstract: A process for coating an edge within a hole in a coated component is provided. The hole is a cooling-air hole operable conduct a coolant therethrough. According to the processes, an outer coating is provided on the outer surface of the component. An inner coating is provided on an inner surface within the hole, wherein the inner coating within the hole takes place using a coating nozzle at a different angle to the coating of the outer surface around the hole, if the spray angles for the outer coating and inner coating relate to the outer surface.

Abstract: A process for setting the average flow rate within a hollow component is provided. The process includes setting a relatively small wall thickness in a first region with a relatively large flow cross section using a first diffusion coating process and setting a relatively large wall thickness by a second different diffusion process in a second region with a relatively small flow cross section. The use of different diffusion coatings in a component allows the flow of coolant through a component to be set in a controlled manner.

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: Ceramic coatings for a component that is subjected to high temperatures, especially for a turbine blade are provided. The ceramic coatings contain one or more compounds that are selected from alkaline earth silicates, ZrV2O7 and Mg3(VO4)2. A layer system including at least one coating of the ceramic coating is also provided.

Abstract: A process for setting the average flow rate within a hollow component is provided. The process includes setting a relatively small wall thickness in a first region with a relatively large flow cross section using a first diffusion coating process and setting a relatively large wall thickness by a second different diffusion process in a second region with a relatively small flow cross section. The use of different diffusion coatings in a component allows the flow of coolant through a component to be set in a controlled manner.

Abstract: A method for adjusting the coolant consumption within actively cooled components is produced. The components include an interior with at least one duct with different regions which have different cross sections of flow. A greater increase in the wall thickness is produced in the region having the smaller cross section of flow by a first diffusion process and a lesser increase in the wall thickness is produced in the region having the larger cross section of flow by a second diffusion process which is different from the first. By using different diffusion coatings in a component, it is possible to adjust the flow of coolant through a component in a controlled way.

Abstract: A process for coating an edge within a hole in a coated component is provided. The hole is a cooling-air hole operable conduct a coolant therethrough. According to the processes, an outer coating is provided on the outer surface of the component. An inner coating is provided on an inner surface within the hole, wherein the inner coating within the hole takes place using a coating nozzle at a different angle to the coating of the outer surface around the hole, if the spray angles for the outer coating and inner coating relate to the outer surface.

Abstract: Bonding agent layers are often used in heat insulation layers in order to improve the bonding of an outer ceramic layer to a metal substrate. A process is provided wherein a MCrAlX or MCrAl alloy is applied to a substrate whereby an outer layer region within the layer is produced using a heat treatment.

Abstract: Ceramic coatings for a component that is subjected to high temperatures, especially for a turbine blade are provided. The ceramic coatings contain one or more compounds that are selected from alkaline earth silicates, ZrV2O7 and Mg3(VO4)2. A layer system including at least one coating of the ceramic coating is also provided.

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: An HS-PVD (high speed physical vapor deposition) or cold spray method for coating a substrate with a bonding agent layer is provided. This method includes generating a particle stream of a coating material, depositing the particle stream on the substrate and subjecting the substrate to a subsequent thermal treatment, wherein powder particles with a larger particle size are added to the particle stream. A device for implementing the method is also provided.

Abstract: Components according to the prior art, to protect against corrosion, have a protective layer, a metal element (for example Al) of this protective layer forming a protective oxide layer. However, this metal element also diffuses into the substrate in an undesired way. The layer system according to the invention includes a metallic blocking layer which prevents this diffusion, the blocking layer including at least one phase of the PdAl2, Ta2Al, NbAl2 or Nb3Al type.

Abstract: A system for bonding layers (1) of different chemical compositions, such as bonding a thermal barrier layer to a metal substrate on a surface of a gas turbine component. A substrate (4) made either of a ceramic material or particularly of a metal super-alloy may be bonded to an outer layer (16) such as a ceramic by means of a fine-grained intermediate layer (7) bonded to the substrate (4), and a coarse-grained layer (10) bonded to the intermediate layer (7) to create a studded surface (9). The fine and coarse layers (7, 10) provide a transition between the substrate (4) and the outer layer (16) for improved bonding between them. The studded surface (9) may provide at least a 20% increase in bonding surface area for the outer layer (16). Additionally, a medium-grained layer (13) may be applied to the studded surface (9) before applying the outer layer(16).

Abstract: In layer systems according to prior art, the adhesion between the layers or between the layers and the substrate is often poor. In the inventive layer system, the surface of the interface between the layers is enlarged such that the connection and adhesion are improved.

Abstract: In the method according to the invention for producing a hollow cast component having an inner coating in at least one cavity, the component is cast from a base material. A casting mold, which comprises at least one mold insert for defining at least one cavity is used for the casting. In the method according to the invention, the coating material for the inner coating of the component is applied to at least one mold insert before the component is cast. The mold insert is then removed from the cavity after the casting.

Abstract: The invention relates to a method of manufacturing a gas-trubine blade and to a turbine blade. First, a hollow, supporting metal blade body is made, in particular by casting, with a multiplicity of, in particular peg-like, elevations on an outer surface of a blade airfoil of the metal blade body. Impact cooling bores are bored between the elevations from the outer surface to the hollow interior space of the metal blade body. A coating is applied which fills the intermediate spaces between the elevations and closes the impact cooling bores. The coating is made of a heat-resistant, removable material. Then, a covering coat is adhered to the metallically bright top sides of the elevations, and the material in the intermediate spaces between the elevations of the metal blade body and the covering coat is then removed.

Abstract: A method for manufacturing a product that includes a metallic basic body with at least one longitudinal duct disposed therein and with a number of transverse ducts branching off from the longitudinal duct. A covering layer lies on the outside of the basic body. The covering layer serves as a protective or adhesive layer. An enrichment layer covers walls of the longitudinal duct and of the transverse ducts and parts of the covering layer. A ceramic heat-insulating layer can also be provided on the outside.

Abstract: The invention relates to an article of manufacture comprising: a substrate composed of a superalloy containing chromium and a base element selected from the group consisting of iron, cobalt, and nickel; and an enrichment layer containing chromium and placed on the substrate. Therein, the enrichment layer comprises a continuous matrix composed of a gamma-phase solid solution of chromium in the base element. The invention also relates to the manufacture of such an article. The article may in particular be a gas turbine component.

Abstract: A product and a method for manufacturing the product include a metallic basic body with at least one longitudinal duct disposed therein and with a number of transverse ducts branching off from the longitudinal duct. A covering layer lies on the outside of the basic body. The covering layer serves as a protective or adhesive layer. An enrichment layer covers walls of the longitudinal duct and of the transverse ducts and parts of the covering layer. A ceramic heat-insulating layer can also be provided on the outside.