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 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: Aluminum diffusion coatings are applied to structural components of titanium alloys by two separate heat treatment steps applied to the component embedded in an aluminum powder. The first heat treatment step is performed at relatively very low temperatures for avoiding an oxygen embrittlement of the structural component by any remainder oxygen. The subsequent diffusion heat treatment is performed at higher temperatures. If desired, a getter material having a high oxygen affinity, is added to the powder mixture in which the structural components are embedded for the first treatment. The getter material binds any remainder oxygen.

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: A method for the manufacturing of a molded member from a ceramic material, including compressing the molded member within an evacuated capsule of a high temperature-resistant glass under a pressure acting thereabout until the molded member attains a non-porous condition. The working materials for the glass capsule are applied to the molded member in a non-vitrified state; and the coated member is subjected to the reaction temperature of the materials under a vacuum until there is formed a cohesive glass layer enveloping the molded member which will constitute the capsule.

Abstract: The present method produces compound materials by an electrolytic deposit. The extraneous, non-soluble matter is suspended in a fine distribution in the electrolyte. The foreign or extraneous matter and the metal are deposited in the absence of gravity, whereby homogeneous compound materials may be produced having a uniform and/or defined particle distribution. The present apparatus includes a closed electrolytic bath container. A gas separator is operatively connected to the bath. Supply and receiving containers may be connected to the bath container.

Abstract: A process for surface treating ceramic parts so as to increase their resistance to oxidation when exposed to high temperatures. The process includes applying a metal coating to the ceramic part, and thereafter heating the part to form a glass surface layer with the metal oxide built into the lattice of the glass layer. The metals employed may be aluminum, magnesium, titanium, lead, zinc, cadmium, or rare-earth elements. The heat treatment is performed in more than one stage.

Abstract: A method of making a ceramic turbine wheel which includes making a ceramic ring, and providing a ceramic disc within the ring by supporting the external periphery of the ring and hot pressing a ceramic powder within the ring. Ceramic blades are then sintered to the external surface of the ring using a layer of metallic silicon between each blade and the ring. The ring and blades are produced by a reaction-sintering process.