Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Wolfgang Eichmann

Thomas Uihlein

Falko Heutling

Karl-Heinz Manier

Markus Uecker

Martin Thoma

Horst Pillhoefer

Stefan Schneiderbanger

Peter Adam

Alexander Gindorf

Annegret Brendel

Rolf Gerstner

Horst Pillhofer

Karl-Heinz Helling

Josef Lachner

Johannes Hartung

Rudolf Selmeier

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

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 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 wear-resistant coating, in particular an erosion-resistant coating for a component that is exposed to fluidic loads, is disclosed. The wear-resistant coating has one or more multilayer systems applied repeatedly to the surface to be coated, where each of the applied multilayer systems has at least four different layers. A first layer of each multilayer system facing the surface to be coated is made of a metallic material adapted to the composition of the component surface to be coated. A second layer applied to the first layer of each multilayer system is made of a metal alloy material adapted to the composition of the component surface to be coated. A third layer applied to the second layer of each multilayer system is made of a gradated metal-ceramic material and a fourth layer applied to the third layer of each multilayer system is made of a nanostructured ceramic material.

Wear-resistant coating and a component having a wear-resistant coating

A protective layer for load-transferring contact surfaces of gas turbine components, especially titanium turbine components is capable to take up alternating loads at higher temperatures. The protective layer is formed of an alloy having the following composition in percent by weight: aluminum (Al) 4-8%; chromium (Cr) 2-5%; iron (Fe) 0-3.5%; and copper (Cu) remainder.

Protecting layer

Structural components (2), such as turbine blades (16) partially to be coated, for example with precious metal coatings, are inserted into a circumferential pocket on a carrier wheel (8), so that surface areas (10, 10A) protruding radially outwardly are presented for a coating operation, for example by vapor deposition, gas diffusion, plasma spraying, or sputtering, while surface portions (9) of the components within the wheel are protected against coating by wheel disks (8A, 8B). The wheel is rotated either continuously or stepwise through an active coating chamber (3). Surfaces to be coated participate in forming first and second walls for enclosing a coating space (11). Other walls of the space (11) are formed by one or two coating sources (12, 13), such as cathode sputterers, whereby the need for screens or masks (4, 14) that form the remaining walls of the space (11) are minimized. The bottom (59) of the space (11) is preferably formed by wall portions (4A) of the turbine blades (16).

Method and apparatus for the partial coating of sets of structural

A process for vapor depositing a metallic interlayer on the surface of a metal component, for example, by sputtering and thereafter depositing an aluminum diffusion coating on the interlayer. The metallic interlayer is vapor deposited on the surface of the component in a noble gas atmosphere, more than one-half of which, in per cent by weight, is composed of noble gases which are heavier than argon. Advantageously, the noble gases can be krypton or xenon. The process can be used with particular advantage for applying protective aluminum diffusion coatings on turbine blades.

Growing community of inventors

Puchheim, Germany

Wolfgang Eichmann