Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Kaco Gmbh & Co. Kg

André Werner

Wilfried Smarsly

Erich Steinhardt

Bernd Daniels

Thomas Hess

Frank Stiehler

Steffen Schlothauer

Manuel Hertter

Heinrich Walter

Michael Strasser

Stephan Klaen

Josef Linska

Natividad Lopez Lavernia

Manfred A Daeubler

Olaf Andersen

Michael Hillen

Katrin Friedberger

Franz Prieschl

Stephan Klän

Jochen Bantel

Roland Lenz

Cris Kostmann

Joachim Schöck

Ralf Hauser

Artur Schüle

Michael Straßer

Uwe Michel

The present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components () of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps:

Repair of worn component surfaces

The present invention relates to a run-in coating for a turbomachine, in particular for an aero engine, to be attached to a seal between a rotor and a stator, wherein the run-in coating comprises a metallic scaffold having interstices which are filled with an inorganic-nonmetallic filler material, and wherein the metallic scaffold is formed from an arrangement of metal fibers (). The invention also relates to a corresponding turbomachine.

Run-in coating based on metal fibers

Disclosed is process for producing a wear-resistant coating on a component. The process comprises providing an electrolyte which contains Co and/or Ni, dispersing first particles comprising hard material particles and/or slip material particles in the electrolyte, dispersing second particles comprising metal alloy particles in which the metal alloy comprises chromium and aluminum in the electrolyte, providing a component to be coated in a bath of the electrolyte which has first and second particles dispersed therein, and electrodepositing a matrix of Co and/or Ni with incorporated first and second particles on the component. A correspondingly produced wear-resistant coating is also disclosed.

Wear-resistant coating produced by electrodeposition and process therefor

The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells (-) connected to one another in the circumferential direction (U), wherein shells adjacent in the axial direction have cross sections opened counter to a throughflow direction (A) and/or a thread axis inclined counter to the throughflow direction.

Turbomachine seal arrangement

A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface.

TiAl blade with surface modification

Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element () with which the blade element is arranged in a receptacle () of the turbomachine. in the region of the fastening element, the blade element has a core region () and an envelope region () which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

Ductile compensation layer for brittle components

A seal configuration () for a turbo machine having a rotor (), wherein the seal configuration () has a sealing element () to create a seal with respect to the rotor () in an installed position and a supporting device (). The supporting device () has, in at least one section of the supporting device, a material () that melts when it comes into contact with the rotating rotor () in the installed position. A turbo machine having a seal configuration () is also provided.

Seal configuration for a turbo machine

Disclosed is a process for producing a wear-resistant layer, in particular on components of gas turbines or aero engines. The process comprises providing a component with a titanium material on at least part of a surface on which the wear-resistant layer is to be produced, applying a solder formed from a cobalt base material to the titanium material, soldering the solder to the titanium material by applying heat and producing at least one diffusion zone between solder and titanium material which comprises intermetallic phases.

Process for producing intermetallic wear-resistant layer for titanium materials

Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element () with which the blade element is arranged in a receptacle () of the turbomachine. In the region of the fastening element, the blade element has a core region () and an envelope region () which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

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

An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.

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Munich, Germany

André Werner