Mtu Aero Engines Gmbh

Manfred A Daeubler

Werner Humhauser

Wilfried Smarsly

Heinrich Walter

André Werner

Klaus Schweitzer

Ulrike Hain

Horst Mueller-Wittek, Legal Representative

Renate Mendritzki, Legal Representative

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 running-in coating for a compressor housing is disclosed. The running-in coating has at least two layers where a first layer is dimensionally stable and at least one additional layer has run-in capability.

Apparatus and method for coating a compressor housing

A running-in coating for gas turbines and a method for production of a running-in coating are provided. The running-in coating serves to seal a radial gap between a housing () of the gas turbine and the rotating blades () themselves, whereby the running-in coating () is applied to the housing. The running-in coating is made from a CoNiCrAIY-hBN material. The CoNiCrAIY-hBN material can be applied by thermal spraying, in particular plasma spraying.

Running-in coating for gas turbines and method for production thereof

A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.

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Dachau, Germany

Manfred A Daeubler