Mtu Aero Engines Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Mtu Aero Engines Ag

Liburdi Engineering Limited

Ab Solut Chemie Gmbh

Karl-Heinz Manier

Thomas Uihlein

Heinrich Walter

Wolfgang Eichmann

Markus Uecker

Gerhard Wydra

Falko Heutling

Michael Strasser

Max Morant

Richard Lange

Ilya Chuprakov

Robert Sparling

Carl-Stefan Thöne

Rolf Gerstner

Horst Pillhöfer

A method for manufacturing an abrasive coating on a gas turbine component, especially on a gas turbine rotor blade tip, comprising at least the following steps: a) providing a gas turbine component, especially a gas turbine rotor blade; b) providing a high temperature melting alloy powder; c) providing abrasive particles; d) providing a low temperature melting alloy powder; e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture; f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, especially to a tip of said turbine rotor blade; g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder is provided.

Method for manufacturing an abrasive coating on a gas turbine component

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

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

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 structural component made of an iron-base alloy is protected against corrosion by a coating which is produced to have three layers. First, a primary coating or first layer is applied, and then a top coating or second layer is applied. An intermediate layer is formed by a reaction between the first and second layers. Specifically, the intermediate layer is formed after application of the primary coating and of the top coating, by a heat treatment within a reaction temperature range in which intermetallic nickel aluminum or cobalt aluminum compounds are formed. A fourth sealing coat is optional. The primary coating is a nickel or cobalt coating. The intermediate layer comprises intermetallic compounds of nickel aluminide or cobalt aluminide formed by the reaction. The top coating is an aluminum base or aluminum alloy base high-temperature lacquer including a binder. Such a combination coating is especially resistant to fretting, oxidation and etching corrosion. The so coated component is suitable especially as a part for gas turbine engine housings.

Iron-base alloy structural component having a corrosion-inhibiting

A structural component made of an iron-base alloy is provided with a corrosion inhibiting coating which has three layers, namely a primary coating or layer, an intermediate layer, and a top coating or layer. A fourth sealing coat is optional. The primary coating is a nickel or cobalt coating. The intermediate layer comprises intermetallic compounds of nickel aluminide or cobalt aluminide. The top coating is an aluminum base or aluminum alloy base high-temperature lacquer including a binder. Such a combination coating is especially resistant to fretting, oxidation and etch corrosion. The component is suitable especially for parts of gas turbine engine housings. The intermediate layer is formed after application of the primary coating and of the top coating, by a heat treatment within a reaction temperature range in which intermetallic nickel aluminum or cobalt aluminum compounds are formed.

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Scheyern, Germany

Karl-Heinz Manier