Siemens Aktiengesellschaft

Man Diesel & Turbo Se

Diffusion Alloys Limited

Other

Man Turbo Ag

Norbert Czech

Friedhelm Schmitz

Sharad Chandra

Adrian Kempster

Knut Halberstadt

Ralph Reiche

Rolf Wilkenhöner

Andre Jeutter

Markus Beukenberg

John Smith

Bruno Deblon

Roland Herzog

Friedheim Schmitz

A hot-gas conducting component for a flow machine has a nickel-base wrought alloy as structural material and a hot gas-side lining made from the group of iron-chromium-aluminum-yttrium alloys and a flow machine having a component of this type.

Hot gas-guided component of a turbomachine

Disclosed is a heat-insulating protective layer for a component located within the hot gas zone of a gas turbine. Said protective layer is composed of an adhesive layer, a diffusion layer, and a ceramic layer which is applied to the high temperature-resistant basic metal of the component. The adhesive layer comprises a metal alloy [MCrAlY (M=Ni, Co)] containing Ni, Co, Cr, Al, Y, the diffusion layer is produced by calorizing the adhesive layer, and the ceramic layer is composed of ZrO2 which is partially stabilized by means of yttrium oxide. One or several chemical metal elements that have a large atomic diameter and are selected among the group comprising Re, W, Si, Hf, and/or Ta are alloyed to the material of the adhesive layer. The adhesive layer has the following chemical composition after being applied: Co 15 to 30 percent, Cr 15 to 25 percent, Al 6 to 13 percent, Y 0.2 to 0.7 percent, Re up to 5 percent, W up to 5 percent, Si up to 3 percent, Hf up to 3 percent, Ta up to 5 percent, the remainder being composed of Ni.

Heat-insulating protective layer for a component located within the hot gas zone of a gas turbine

A method is provided for coating a hollow, internally cooled blade () of a gas turbine, in which method an outer coating () comprising an MCrAlY-based bonding layer () and a ceramic thermal barrier layer () of zirconium oxide is applied to the base material () of the blade () on the outer side of the blade () and an inner coating () comprising a Cr diffusion layer () is applied to the base material () of the blade () on the inner side of the blade (). The MCrAlY-based bonding layer () is thereby applied to the finished blade (). At the same time, along with the inner coating (), the Cr diffusion layer () is also applied to the MCrAlY-based bonding layer () of the outer coating () by chemical vapor deposition. Subsequently, an Al diffusion layer () and an outer brittle Al build-up layer are applied by chemical vapor deposition to the bonding layer () coated with the Cr diffusion layer (). After that, the outer brittle Al build-up layer is removed by an abrasive treatment and the ceramic thermal barrier layer () is applied to the Al diffusion layer ().

Method for coating a blade and blade of a gas turbine

To protect a base metal layer () against high-temperature corrosion and high-temperature erosion, an adhesive layer () based on MCrAlY is applied to the base metal layer (). The adhesive layer () is coated with an Al diffusion layer () by alitizing. The diffusion layer () is subjected to an abrasive treatment, so that the outer built-up layer () on the diffusion layer () prepared by alitizing is removed by the abrasive treatment. A ceramic heat insulation layer () consisting of zirconium oxide, which is partially stabilized by yttrium oxide, is applied to the diffusion layer () thus treated.

Process for applying a protective layer

The invention relates to a method for removing an area of a layer of a component consisting of metal or a metal compound. According to prior art, corrosion products of a component are removed in a first step by applying a molten mass or by heating in a voluminous powder bed. This requires high temperatures or a large amount of space. The inventive method for removing corrosion products of a component is characterized in that a cleaning agent is applied locally, which removes the corrosion products by means of a gaseous reaction product.

Method for removing at least one area of a layer of a component consisting of metal or a metal compound

A process for machining the interior of a hollow component for high-temperature application is described. The component has a base body made from a base material, and is in particular a blade of a gas turbine. The component has a cavity, in particular cooling channels for cooling air to flow through, which is provided with an internal coating. According to the process, a treating fluid flows through the cavity, solid particles with an abrasive action being added to the treating fluid.

Process for treating the interior of a hollow component

A nickel-base alloy containing a continuous matrix composed of a solid solution of chromium in nickel and a precipitate granularly dispersed in and coherent with the matrix and composed of an intermetallic nickel compound. The intermetallic nickel compound contains gallium that replaces aluminum and/or titanium partly or completely. The invention also relates to an article of manufacture containing a substrate formed of such a nickel-base alloy.

Nickel-base alloy and article manufactured thereof

The invention relates to a high-temperature-resistant component comprising a nickel-based or cobalt-based superalloy, in particular having a protective alloy selected from the class consisting of MCrAlY alloys. The component has an antioxidation coating comprising gallium. The invention also relates to a corresponding method of providing protection against oxidation.

High-temperature-resistant component and method of providing protection thereof against oxidation

A corroded superalloy or heat resistant steel part, in particular a gas turbine component like a gas turbine blade, having a surface with products or corrosion is refurbished. The invention the surface is cleaned, in particular mechanically or chemically, and an aluminide coating is applied to the cleaned surface. Subsequently, the aluminide coating is removed, whereby all products of corrosion which have still remained in the part to be refurbished are removed as well.

Refurbishing of corroded superalloy or heat resistant steel parts

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.

Method for manufacturing a product with a metallic basic body

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.

Article having a superalloy substrate and an enrichment layer placed

A protective coating for protecting a component from corrosion and oxidation at a high temperature and from excessive thermal stress, has a heat insulation layer including a ceramic material and an adhesion-promoting layer including a rhenium containing metal alloy. The metal alloy belongs to the alloys covered by the general term MCrAlY, where M represents cobalt and/or nickel and Y represents yttrium and/or at least one equivalent metal from the group including scandium and the rare earth elements. The protective coating is distinguished by high oxidation resistance and corrosion resistance of the alloy, by outstanding thermal fatigue properties and an effective and permanent bond between the alloy and the ceramic heat insulation layer. As a result of the heat insulation, the temperature at the outer surface of the protective coating can be considerably higher than with purely metallic protective coatings, without an increased thermal load being exerted on the component. The protective coating is therefore particularly suitable for a gas turbine component exposed to a hot combustion gas, for example a guide vane, a rotor blade or a heat shield.

Protective coating for protecting a component from corrosion, oxidation

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.

Product with a metallic basic body and method for manufacturing a product

An article that is used to transport a hot oxidizing gas, in particular a flue gas in a gas turbine, has a surface acted upon by the gas. This surface is formed by an alloy which has 10 to 40 wt. % chrome, 1 to 20 wt. % gallium and optionally other specific elements in a base including at least one element from the group of iron, cobalt and nickel. In the alloy the gallium replaces aluminum and/or silicon. The alloy is deposited especially as a protective layer on a superalloy substrate and optionally coated with a gas-permeable ceramic layer.

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Dorsten, Germany

Norbert Czech