Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Daimler Chrysler Ag

Falko Heutling

Thomas Uihlein

Wolfgang Eichmann

Joachim Bamberg

Stefan Schneiderbanger

Bertram Kopperger

Alexander Gindorf

Markus Uecker

Karl-Heinz Manier

Gerhard Andrees

Dietmar Helm

Klaus-Dieter Tartsch

Heiko Fietzek

Juergen Wehr

Claudia Kunze

Ulrike Habel

Josef Lachner

Annegret Brendel

Josef Mayr

Wilfried Smarsly

A method for producing a forged component from a TiAl alloy is provided, in particular a turbine blade (), in which method a blank of a TiAl alloy is provided and deformed by forging into a forged, semi-finished part (). A usable volume is defined within the forged, semi-finished part, the usable volume corresponding to the forged component to be produced. The shape of the blank is selected such that within the usable volume of the forged, semi-finished part, the degree of deformation resulting from forging deviates by no more than &#xb1;1 from a defined value.

Method for producing forged TiAl components

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

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

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 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

A blade of a turbomachine such as a gas turbine includes a blade vane with a blade tip and a blade base. A blade tip armor cladding is applied on the blade tip. A coating covers at least the armor cladding and includes at least one multilayer coating system, and preferably plural such coating systems stacked repetitively on one another. Each coating system includes at least two different layers stacked successively on one another, with one layer of a metal material closer to the blade tip and one layer of a ceramic material farther from the blade tip.

Turbomachine blade with a blade tip armor cladding

A composite material is formed of several assembled discs of matrix material, wherein each disc preferably has at least one groove therein, and at least one fiber () is inserted in each groove. A composite of matrix material and fibers () is present in an inner section (), whereas exclusively the matrix material is present in an outer section (). The inner section with the fibers () reaches to different radial extents toward the outer section (), to achieve a strength-optimizing intermeshing of the inner section () with the outer section ().

Composite material, method for the production of a composite material and the utilization thereof

A process for is producing a fiber-reinforced semifinished product in the form of metal strips, metal sheets etc., from at least one layer of fibers which includes a number of long to endless reinforcing fibers spaced apart from one another and arranged in parallel and a metal. A metal jacket applied to the reinforcing fiber by a PVD process (physical vapor deposition) may act for example as the metal. At least certain regions of the metal and the reinforcing fibers run through a welding process in which a bonding takes place by planar melting of the metal to form a matrix surrounding the reinforcing fibers.

Process for producing a fiber-reinforced semifinished product in the form of metal strips, metal sheets or the like and apparatus for carrying out the process

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Munich, Germany

Falko Heutling