Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Mtu Motoren-Und Turbinen-Union Munchen Gmbh

Ab Solut Chemie Gmbh

Thomas Uihlein

Wolfgang Eichmann

Falko Heutling

Ralf Stolle

Karl-Heinz Manier

Markus Uecker

Hans Weber

Erwin Bayer

Hermann Klingels

Erich Steinhardt

Norbert Legrand

Herbert Fischer

Erwin Fischhaber

Werner Humhauser

Heinrich Walter

Stefan Schneiderbanger

Alexander Gindorf

Ulrich Knott

Michael Schober

Michael Strasser

Wilhelm Hoffmuller

Jürgen Rösing

Josef Linska

Josef Eichner

Frank Seidel

Bernd Kriegl

Lutz Winkler

Joerg Windprechtinger

Dietmar Helm

Martin Dürr

Fabian Moritz

Wolfgang Wachter

Markus Gether

Rolf Gerstner

Johannes Schr&ouml;der

Robert Sigl

Johannes Schroder

Andreas Kaehny

Josef Lachner

Werner Moosrainer

Annegret Brendel

Carl-Stefan Thöne

Philipp Utz

Jörg Windprechtinger

A blade for a turbomachine is provided. The blade at its blade tip () includes blade tip armor (), and an erosion protection layer () above the blade tip armor. For the blade, the erosion protection layer in the area of the blade tip has a layer thickness in the range of 5 μm to 100 μm, in particular 10 μm to 50 μm.

Blade for a turbomachine including blade tip armor and an erosion protection layer, and method for manufacturing same

A method for manufacturing a blade () for a turbomachine, the blade having a hardfacing on its tip () and an erosion-protection coating () at least on its airfoil () is provided. Initially, a blade tip hardfacing is applied to the blade tip and, subsequently, a mask () is positioned in the region of the blade tip hardfacing, the mask covering the blade tip hardfacing, and, subsequently, the erosion-protection coating is deposited. The mask is removed after the erosion-protection coating is completed. A blade for a turbomachine, the blade having a hardfacing on its tip () and an erosion-protection coating () at least on its airfoil () is also provided. The erosion-protection coating at least partially covers the blade tip hardfacing, and the thickness of the erosion-protection coating decreases continuously in and/or toward the region of the blade tip hardfacing.

Masking method for producing a combination of blade tip hardfacing and erosion-protection coating

The present invention relates to a method for producing a blade or blade arrangement of a turbomachine, which features the following steps: Furthermore, the invention relates to correspondingly produced blades or blade arrangements.

Method of producing blades or blade arrangements of a turbomachine with erosion protection layers and correspondingly produced component

The invention relates to an erosion protection coating (), in particular, for gas turbine components, having a horizontally segmented and/or multi-layered construction. i.e., having at least one relatively hard layer () and having at least one relatively soft layer (), wherein the relatively hard layer or each relatively hard layer as well as the relatively soft layer or each relatively soft layer are disposed on top of one another in an alternating manner, in such a way that an outer-lying layer, which forms an outer surface of the erosion protection coating, is formed as a relatively hard layer (). According to the invention, the relatively hard layer or each relatively hard layer () as well as the relatively soft layer or each relatively soft layer () are formed as a ceramic layer in each case.

Erosion protection 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

The invention relates to a method for cleaning a turbo-machine stage () consisting of at least one of the following steps: a cleaning nozzle () is introduced into an opening of a turbo-machine, in particular into an inspection opening (); and the blade () of the stage is acted upon by solid particles, said particles subliming at the blade temperature, in particular into dry ice particles.

Cleaning of a turbo-machine stage

The invention relates to an anti-wear coating, specifically for components which are subject to erosion under mechanical loading, in particular for gas turbine components, said coating comprising at least two different individual layers which preferably alternate with one another multiply and are applied to a surface of a component which is to be coated. The individual layers comprise a ceramic main layer () and a quasi-ductile, non-metallic intermediate layer ().

Anti-wear coating

A method for removing the coating from a gas turbine component, namely for the complete or partial removal of a multilayer wear protection coating from the surface of the gas turbine component, the wear protection coating having at least one relatively hard ceramic layer and at least one relatively soft metallic layer, wherein, in order to remove the multilayer wear protection coating, the gas turbine component is alternately positioned in two different chemical baths, a first bath being used exclusively for the removal of each relatively hard ceramic layer, and a second bath being used exclusively for the removal of each relatively soft metallic layer of the wear protection coating.

Method for removing the coating from a gas turbine component

The present invention relates to methods for joining a rotationally asymmetrical part, preferably a turbine blade, which is made of a monocrystalline material, to a part, preferably a rotor core, which is made of polycrystalline material, having the method steps of: &#x2014;joining the rotationally asymmetrical part to an adapter piece made of polycrystalline material by means of rotational friction welding, and &#x2014;joining the adapter piece to the part made of polycrystalline material. The present invention also relates to a turbine blisk having a rotor core made of polycrystalline material and turbine blades made of monocrystalline material.

Methods for joining a monocrystalline part to a polycrystalline part by means of an adapter piece made of polycrystalline material

A method for manufacturing an integrally bladed rotor (), in particular for a gas turbine, including the following method steps: preparing a rotor base member () having at least one first weld surface () and one blade () having a second weld surface (); positioning the rotor base member () and the blade () in such a way that a join zone () is formed between the first and second weld surface (); and filling the join zone () with metal powder () and the laser welding or electron beam welding of the metal powder (). An integrally bladed rotor () has a join zone () between the rotor base member () and blades (), the join zone () being filled with welded metal powder ().

Method for the production of an integrally bladed rotor, and rotor

For producing a component, especially a gas turbine component, coated with a wear-protection, corrosion-protection or erosion-protection coating, a method includes the following steps: providing a component () to be coated on a component surface (); at least partially coating the component () on its component surface with an at least two-layered protective coating (), which includes at least one relatively soft layer () and at least one relatively hard layer (); and then surface densifying the at least partially coated component on its coated component surface by ball blasting or shot peening.

Method for producing a component covered with a wear-resistant coating

An anti-wear coating, in particular an anti-erosion coating, which is applied to a surface of a component that is stressed under fluid technology and is to be protected, in particular a gas turbine part, is disclosed. The anti-wear coating includes one or more multilayer systems applied in a repeating order to the surface to be coated, and the/each multilayer system includes at least one relatively soft metallic layer and at least one relatively hard ceramic layer. All the layers of the/each multilayer system are based on chromium, and a diffusion barrier layer is applied between the surface to be protected and the multilayer system(s).

Anti-wear coating and component comprising an anti-wear coating

The invention relates to a method for producing a blade tip plating () on a blade () for a turbomachine, in particular on a high-pressure rotating compressor blade for a gas turbine, comprising the following steps: &#x2014;producing a particle composite material () having embedded hard material particles (); &#x2014;placing the panicle composite material () on a solder () applied to the blade tip (); and&#x2014;healing the solder ().

Method for producing a blade plating on a blade for a turbomachine

A thermal barrier layer for metallic components, in particular for gas turbine components which are subject to high temperatures or hot gas, is disclosed. The thermal barrier layer includes an inner contact layer and an outer top layer, where the inner contact layer is applied to a surface of the component via an adhesion-promoting layer that is disposed therebetween, and between the outer top layer and the inner contact layer an intermediate layer is formed.

Thermal barrier layer

The present technology generally relates to a wear-resistant coating, especially for gas turbine components, comprising a horizontally segmented or multilayered structure, i.e. at least one relatively hard, ceramic layer and at least one relatively soft, metallic layer. The ceramic layer and the metallic layer are alternately arranged on top of each other in such a way that an external layer forming an external surface of the wear-resistant coating is embodied as a ceramic layer. According to the invention, at least the external, ceramic layer is segmented in a column-type manner in a vertical direction.

Wear-resistant coating

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Dachau, Germany

Thomas Uihlein