Abstract: A component having a platinum-aluminum substrate surface region which is formed in the area of the substrate surface of the component by diffusion of platinum and aluminum into the substrate surface and which contains platinum and aluminum as well as the constituents of the substrate composition. The integrated aluminum content and/or the integrated platinum content in the substrate area is less than 18 wt %.

Abstract: A component having a platinum-aluminum substrate surface region which is formed in the area of the substrate surface of the component by diffusion of platinum and aluminum into the substrate surface and which contains platinum and aluminum as well as the constituents of the substrate composition. The integrated aluminum content and/or the integrated platinum content in the substrate area is less than 18 wt %.

Abstract: A layer system for the rotor/stator seal of a turbomachine, in particular of a gas turbine, is applied to a metallic component and can be run in with respect to a further component which can move relative to the metallic component, which, in order to improve the service life and run-in properties, is characterized by a bonding layer which is applied to the metallic component and a run-in coating which is applied to the bonding layer and comprises at least two layers, the first layer, which adjoins the bonding layer, being harder than the second layer, and the second layer having run-in properties.

Abstract: In a turbine blade for a gas-turbine engine impeller, which is rotationally mounted in a housing, the turbine blade has a blade tip, a leading-edge positioned upstream in the direction of flow, and trailing edge positioned downstream, and includes a blade section, which has a section depth parallel to the direction of flow and a section thickness parallel to the direction of travel of the turbine blade. An abrasive coating, which has an effective length corresponding to the section thickness along the section depth, is applied to the blade tip, the abrasive coating of the blade tip brushing against an abrasion coating, which is introduced into the surrounding housing. Along the section depth, in particular in the region of the leading and trailing edges, the abrasive coating coming into contact with the abrasion coating has an effective length, which may always, continually or very frequently be greater, but at least equal to a predefined, minimum dimension.

Abstract: A layer system for the rotor/stator seal of a turbomachine, in particular of a gas turbine, is applied to a metallic component and can be run in with respect to a further component which can move relative to the metallic component, which, in order to improve the service life and run-in properties, is characterized by a bonding layer which is applied to the metallic component and a run-in coating which is applied to the bonding layer and comprises at least two layers, the first layer, which adjoins the bonding layer, being harder than the second layer, and the second layer having run-in properties.

Abstract: In a turbine blade for a gas-turbine engine impeller, which is rotationally mounted in a housing, the turbine blade has a blade tip, a leading-edge positioned upstream in the direction of flow, and trailing edge positioned downstream, and includes a blade section, which has a section depth parallel to the direction of flow and a section thickness parallel to the direction of travel of the turbine blade. An abrasive coating, which has an effective length corresponding to the section thickness along the section depth, is applied to the blade tip, the abrasive coating of the blade tip brushing against an abrasion coating, which is introduced into the surrounding housing. Along the section depth, in particular in the region of the leading and trailing edges, the abrasive coating coming into contact with the abrasion coating has an effective length, which may always, continually or very frequently be greater, but at least equal to a predefined, minimum dimension.

Abstract: A component made of an intermetallic compound of titanium and aluminum, or of alloys of such intermetallic compounds with alloying additions forming the base material, and with an aluminum diffusion coating on the base material, is provided. The component has, between the base material and the aluminum diffusion coating, a closed zone which is close to the surface and has a recrystallization structure. For this purpose, the component is cold-formed or slightly melted in a zone which is close to the surface, is then annealed at the recrystallization temperature, and finally has an aluminum diffusion coating applied to the recrystallized zone. The process is used for components in engines and, particularly, for components in the hot-gas duct of an engine.

Abstract: A device for coating hollow workpieces made of heat-resistant alloys, such as Ni, Co or Fe base alloy via gas diffusion is provided. The outer and inner surfaces of the workpieces are linked with one another by bores. The workpieces are arranged in a container which is located in a processing chamber. The workpiece holders are arranged at a geodetically low height with respect to a donor metal body. The donor metal body made of granulates, sintered metal or compact metal completely surrounds the outer surfaces of each workpiece to be coated while maintaining a gap. The device is suitable for the inner and outer coating of power unit blades with cooling air bores.

Abstract: A structural component of titanium or titanium alloy is provided with a protective coating made substantially of an oxidation resistant and diffusion inhibiting base layer (2), an intermediate layer (3) forming a titanium fire inhibiting layer, and a cover layer (4) forming a passivating sealing layer. These layers are applied by various methods.

Abstract: A structural component of titanium or titanium alloy is provided with a protective coating made substantially of an oxidation resistant and diffusion inhibiting base layer (2), an intermediate layer (3) forming a titanium fire inhibiting layer, and a cover layer (4) forming a passivating sealing layer. These layers are applied by various methods.

Abstract: The quality or durability of an oxidation protective coating produced by alitizing or aluminizing on the surface of a structural component made of titanium or titanium alloy, is improved by adding niobium to the surface of the structural component. The addition may be accomplished prior to the aluminizing or during the aluminizing. Prior application may involve, for example, vapor deposition of the niobium. Simultaneous application involves including a niobium donator powder in the aluminizing powder mixture.

Abstract: Device for the differential cooling or temperature control of inside and outside walls or wall areas of a component, more particularly of a turbomachine component. The device has nozzle arrays or spray pipes under locally separate and/or phased control for the admission of thermally controlled medium. Use of various media and differential temperatures and pressures. Transportation of the component from treatment station to treatment station in its passage.