Siemens Aktiengesellschaft

Knut Halberstadt

Norbert Czech

Werner Stamm

Jens Birkner

Fathi Ahmad

Eckart Schumann

Francis-Jurjen Ladru

Christian Lerner

Beate Heimberg

Adrian Kempster

Rainer Nies

Sascha Martin Kyeck

Walter David

Bernhard Siebert

Rudolf Gensler

John Smith

Arne Grassmann

Bora Kocdemir

Jörg SCHÜRHOFF

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.

Setting the quantity of cooling air for a turbine blade or vane by controlled overspray

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.

Method for assessing the coolant consumption within actively cooled components

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, ZrVOand Mg(VO). A layer system including at least one coating of the ceramic coating is also provided.

Ceramic heat-insulating layers having increased corrosion resistance to contaminated fuels

A system for bonding layers () 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 () made either of a ceramic material or particularly of a metal super-alloy may be bonded to an outer layer () such as a ceramic by means of a fine-grained intermediate layer () bonded to the substrate (), and a coarse-grained layer () bonded to the intermediate layer () to create a studded surface (). The fine and coarse layers () provide a transition between the substrate () and the outer layer () for improved bonding between them. The studded surface () may provide at least a 20% increase in bonding surface area for the outer layer (). Additionally, a medium-grained layer () may be applied to the studded surface () before applying the outer layer().

Layer system

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.

Gas-turbine blade and method of manufacturing a gas-turbine blade

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 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.

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Mülheim an der Ruhr, Germany

Knut Halberstadt