Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Frank Seidel

Jürgen Rösing

Nils Weidlich

Thomas Uihlein

Bernd Kriegl

Markus Waltemathe

Lutz Winkler

Philipp Doebber

Martin Dürr

Fabian Moritz

Leszek Zak

Harald Krappitz

Bastian Mania

Alexandre Minso

Matthias Wagner

The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (), restoring the blade tip reinforcement (), and restoring the blade coating in the region of the repaired blade tip (). The invention furthermore relates to a device for carrying out such a method.

Method and device for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating

Disclosed is a thermal barrier coating system for components of a turbomachine, especially for high temperature-stressed or hot gas-stressed components of a turbomachine, comprising a ceramic coating of fully or partially stabilized zirconium oxide, and an oxide cover coating which comprises aluminum and at least one element from the group lanthanum, magnesium, silicon, calcium and sodium. The aluminum oxide exists at least partially as free &#x3b1;-AlO. Also disclosed is a method for producing a corresponding thermal barrier coating system.

Thermal barrier coating with high corrosion resistance

Disclosed is a method of repairing damage of an aircraft engine component made of or comprising weldable thermoplastic material, which method comprises welding of the weld filler material into an initially prepared damaged area. Also disclosed are the use of plastic welding technique for repairing damaged aircraft engine components made of weldable thermoplastic materials.

Method of repairing damage of aircraft engine components made of weldable thermoplastic materials

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

Solder alloy based on nickel is composed of a mixture with a first soldering material, a second soldering material, and a base material, wherein the base material is a nickel-based material which corresponds to the material to be soldered and is present in a proportion of 45-70% by weight in the mixture, the first soldering material is a nickel-based material including chromium, cobalt, tantalum, aluminum and boron, and is present in a proportion of 15-30% by weight in the mixture, and the second soldering material is a nickel-based material including chromium, cobalt, molybdenum, tungsten, boron and hafnium, and is present in a proportion of 15-25% by weight in the mixture.

Nickel-based solder alloy

Growing community of inventors

Grossburgwedel, Germany

Frank Seidel