Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Karl-Heinz Dusel

Thomas Hess

Erwin Bayer

Wilhelm Satzger

Andreas Jakimov

Siegfried Sikorski

Hans-Christian Melzer

Roland Huttner

Bertram Kopperger

Peter Seitz

Manfred Feldmann

Rudolf Stanka

Joachim Bamberg

Albin Platz

Herbert Hanrieder

Steffen Schlothauer

Reinhold Meier

Manuel Hertter

Christian Liebl

Georg Schlick

Stefan Schneiderbanger

Alexander Ladewig

Karl Maar

Carsten Butz

Wilhelm Meir

Klaus Broichhausen

Markus Waltemathe

Josef Waermann

Laura Buerger

Michael Mücke

Laura Bürger

Thomas Heß

Josef WÄRMANN

Wilhelm Meier

Stefan Neuhäusler

Claus MÜLLER

The invention relates to a method and device for generatively producing components, said device comprising a radiation device for selectively radiating a powder bed, and an induction device for inductively heating the component produced by radiating the powder bed, Said induction device comprising at least one voltage source which can simultaneously produce alternating voltages with at least two different frequencies.

Multi-frequency induction heating of generatively produced components

In a method for the generative production of a component (), in particular of a turbo-engine component, wherein material () is bonded layer-by-layer selectively to a layer disposed therebeneath or to a substrate (), according to the invention a laser (A;B;) additionally acts on the material () before, during and/or after the bonding.

Method and device for the generative production of a component using a laser beam and corresponding turbo-engine component

The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit.

Device for producing, repairing and/or replacing a component by means of a powder that can be solidified by energy radiation, method and component produced according to said method

The invention relates to a method for the additive manufacture of at least one region of a component. Here, at least the following steps are carried out: a) layer-wise application of at least one powder-form component material onto a component platform in the region of a build-up and joining zone; b) layer-wise and local solidifying of the component material by selective exposure of the component material by at least one high-energy beam in the region of the build-up and joining zone, with the formation of a component layer; c) layer- wise lowering of the component platform by a pre-defined layer thickness; and d) repeating steps a) to c) until the component region or the component has been completely fabricated.

Method and device for the additive manufacture of at least one component region of a component

Disclosed is a method for monitoring a generative fabrication process in which a component is formed in an installation space from a multiplicity of layers by using a three-dimensional data model and a following layer is fixed to a preceding layer by means of a high-energy beam. The method comprises detecting the component at least optically and detecting the installation space thermally during layer application. Also disclosed is a device for carrying out the method.

Method and device for process monitoring

The invention relates to a sealing arrangement, a guide vane arrangement, and a turbomachinewith such a sealing arrangement, wherein the sealing arrangementis designed for a guide vane ringof a turbomachine, wherein the sealing arrangementcomprises a thin-walled annular structurethat is substantially closed on all sides, and wherein the annular structuredelimits an annular interior space, wherein a hollow cell structure, which is designed so as to mechanically support the annular structure, is provided in the annular interior space

Sealing arrangement for a turbomachine, a guide vane arrangement, and a turbomachine with such a sealing arrangement

A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.

Damping device for being situated between a housing wall and a casing ring of a housing of a thermal gas turbine

A method for producing a thin-walled structural component from a casting material. The casting material is supplied as a powder, and the powder is deposited on a support () by a kinetic cold gas spraying process so as to form the structural component ('). A structural component which is made of a casting material and in which the structure is formed from a plurality of particles () that are interlinked and deformed using a cold gas spraying process.

Thin-walled structural component, and method for the production thereof

A method for repairing gas turbine components, in particular gas turbine blades, including at least the following steps: a) preparing a gas turbine component to be repaired; b) removing a damaged portion from the gas turbine component to be repaired, thereby forming a plane separation surface; c) placing the gas turbine component at least partly in a process chamber in such a way that the plane separation surface extends approximately horizontally within the process chamber; d) filling the process chamber with a metal powder that is bonding-compatible with the material of the gas turbine component to be repaired, namely up to the level of the separation surface; e) building up the removed portion on the separation surface by depositing metal powder in layers onto the separation surface and by fusing the metal powder, which has been deposited in layers onto the separation surface, to the separation surface.

Repair method

A gas turbine having at least one compressor, at least one combustion chamber, and at least one turbine, the or each compressor and/or the or each turbine having a rotor that includes rotor blades surrounded by a stationary housing, and a run-in coating being assigned to the housing is disclosed. The gas turbine includes at least one channel which is configured to apply a pressure prevailing on the high-pressure side of the blades of a rotor to a low-pressure side of the same in the area of a gap between the radially outer ends of the blades and the housing and thereby prevent a flow through the gap.

Gas turbine having a peripheral ring segment including a recirculation channel

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Unterschleissheim, Germany

Karl-Heinz Dusel