Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Mtu Motoren-und Turbinen-union

Other

Heinrich Walter

Horst Pillhoefer

Michael Strasser

Lothar Peichl

Martin Thoma

Peter Adam

Frank Brungs

Martin Schaipp

Ralph Kropp

Horst Pillhofer

Thomas Uihlein

Stefan Schneiderbanger

André Werner

Richard Grunke

Michael Schober

Karl-Heinz Manier

Josef Linska

Ralf Stolle

Max Morant

Manfred A Daeubler

Anja Kliewe

Markus Niedermeier

Raimund Lackermeier

Werner Moosrainer

Max Kraus

Nicole Jakimov

Karlheinz Manier

Richard Lange

Ernst Affeldt

Andreas Kaehny

Josef Lachner

Jörn Kohlscheen

Jorn Kohlscheen

Horst Pillhöfer

Nicole Barl

The present invention relates to a component of a turbomachine made of a composite material comprising a ceramic matrix and a corrosion protection layer arranged on the composite material. The corrosion protection layer comprises: 50-80 wt % silicon, 12-30 wt % nitrogen, 2-8 wt % oxygen, 2-8 wt % aluminum, and 0-3 wt % of at least one alkaline earth metal. The invention furthermore relates to a method for producing a corresponding component of a turbomachine.

Composite ceramic comprising a corrosion protection layer and production method

A method for coating a turbine blade of a gas turbine is disclosed. The method includes applying a lacquer coat to a region of the turbine blade, where the lacquer coat includes chromium particles and/or chromium alloy particles, halides, and a binding agent. The method further includes drying the applied lacquer coat at a temperature between 50&#xb0; C. and 600&#xb0; C. with disintegration of the binding agent and subsequent reactive connection at a temperature between 900&#xb0; C. and 1160&#xb0; C.

Turbine blade of a gas turbine and method for coating a turbine blade of a gas turbine

Disclosed is a process for producing a high-temperature protective coating for metallic components, in particular components of turbomachines which are subjected to thermal loading. The process comprises producing a slip from MCrAlY powder, in which M is at least one metal, and from a Cr powder, applying the slip to the component to be coated and subsequently alitizing the component provided with the slip.

Process for producing a high-temperature protective coating

A method and device for partially masking a component or assembly during a coating process, the device including at least one masking plate for separating a region to be coated from a region to be masked, the masking plate having at least a portion of at least one opening which conforms closely to the contour of the component and is adapted to allow passage of the component therethrough is provided. In masked region, a gap is present along opening, at least one sealing element being disposed at the gap on the side of the masked region.

Device and method for partially masking a component zone of a component

A method for repairing run-in coatings is provided. The method includes the steps of filling a damaged site of the run-in coating with a filling material having a material composition that corresponds to a material composition of the run-in coating or is comparable to the material composition of the run-in coating or having material properties that are comparable to material properties of the run-in coating; drying the filling material that has been filled into the damaged site; depositing a donor diffusion layer over an area of the damaged site and onto the dried filling material; and thermally treating the run-in coating at least in the area of the damaged site to locally diffuse at least one metallic element from the donor diffusion layer into the filling material.

Method of repairing run-in coatings

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 %.

Component with a platinum-aluminum substrate area, platinum-aluminum coating and production method

A process for chroming an inner surface of a component, in which the inner surface which is to be coated is not brought into contact with a powder which forms the coating gas, includes: providing a mixture of chromium granules and an activator; heating the mixture to a temperature at which a coating gas which substantially comprises gaseous CrCl is formed; dissipating the coating gas; and exposing the inner surface of the component to the coating gas thereby forming a chromium-containing diffusion layer.

Process and apparatus for chroming an inner surface of a component

In a gas phase coating process for coating turbines blades or housing parts, one or more workpieces to be coated are arranged in a container that is heated. Propellant is supplied to the container via a propellant pipe. A donor substance is arranged at the floor of the container together with an activator and forms a coating gas that is circulated pulse-like in the interior of the container by means for circulation, for example, a Venturi nozzle from which the propellant emerges.

Gas phase coating process and apparatus for gas-phase coating of workpieces

A method for selectively protecting a component made of an iron-base alloy, cobalt-base alloy or nickel-base alloy with a protective arrangement which protects select areas of the component from aluminizing or chromizing during gas diffusion coating, wherein a first layer acts as an interlayer and a second layer acts as a getter layer for reaction gases. The method comprises the steps of depositing a first layer of slip cast material comprising oxide ceramic particles carried in a low-carbon, halide free, liquid vehicle; depositing a second layer comprising metal or a metallic slip, which comprises at least 50% by weight of the base metal of the component and all major alloy constituents of the component; aluminizing or chromizing by gas diffusion coating; and removing the protective arrangement from the component.

Method of manufacturing a component with a protective arrangement which

This invention relates to a component of an iron, cobalt or nickel-base alloy with a protective arrangement to prevent aluminizing or chromizing during gas diffusion coating, with a first layer as an interlayer and a second layer as a getter layer for reaction gases, where the first layer is a slip casting layer composed of oxide ceramic particles carried in a low-carbon vehicle free from halide, and the second layer is a metal layer or a metallic slip casting layer. The metal layer contains at least 50% by weight of the base-metal fraction of the component and exhibits all major alloy constituents of the component. The metal layer may be a sintered metal shape.

Component with protective arrangement to prevent aluminizing or

Inner and outer surfaces of structural components are aluminized by an aluminum gas diffusion process. For this purpose a gas mixture of a halogenous gas, aluminum monohalide gas, hydrogen, and negligible proportions of aluminum trihalide gas is caused to flow over the outer and inner surfaces of the component to be coated. The process is performed in a vessel in which at least two different temperature zones are maintained for keeping one or more aluminum sources at a higher temperature than the component to be coated. Especially gas turbine engine blades are protected against oxidation and corrosion by the so formed aluminum diffusion coatings on outer and inner surfaces of the blades.

Method for coating a structural component by gas diffusion

Device for coating hollow workpieces by gas diffusion

Method and apparatus for coating a structural component by gas diffusion

A method for the powder pack coating of hollow structural components is performed with spherical powder particles of a donor metal in which the hollow component is embedded. During the embedding, the component is subjected to a tumbling motion about several spatial axes to fill all cavities in the component. After the powder pack coating process the cavities of the component are cleared of any excess powder particles under the action of a gas stream. This method is suitable especially for coating engine blades having cooling ducts and cooling air holes, such as turbine blades. The effect of the forced air flow through the internal cavities for the removal of excess powder out of the hollow component is enhanced by simultaneously vibrating the component.

Method for the powder pack coating of hollow bodies

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.

Method for producing a layer protective against oxidation

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Friedberg, Germany

Heinrich Walter