Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Mtu Motoren-und Turbinen-union Munchen Gmbh

Other

Airbus Operations Gmbh

Daimler Chrysler Ag

Eads Deutschland Gmbh

Sonats

Dorner

Fag Aerospace Gmbh & Co. Kg

Eads France Sas

Erwin Bayer

Albin Platz

Martin Bussmann

Juergen Steinwandel

Thomas Hess

Thomas Kraenzler

Peter Geiger

Thomas Dautl

Bertram Kopperger

Thomas Peschke

Andreas Jakimov

Karl-Heinz Dusel

Holger Polanetzki

Karl-Hermann Richter

Joachim Bamberg

Jürgen Steinwandel

Max Niegl

Ludwig Steinhauser

Wilfried Smarsly

Roland Huttner

Manuel Hertter

Stefan Schneiderbanger

Manfred Feldmann

Rudolf Stanka

Wilhelm Satzger

Peter Adam

Ulrich Knott

Horst Pillhoefer

Peter Jaenker

Herbert Hanrieder

Thomas Uihlein

Boris Grohmann

Siegfried Sikorski

Gerhard Wydra

Emmanuel Joubert

Petra Kufner

Edgar Streit

Martin Fessler-Knobel

Joerg Hoeschele

Patrick Cheppe

Thomas Herzinger

Juergen Kraus

Alexander Gindorf

Jean-Michel Duchazeaubeneix

Wolfgang Becker

Frank Hermle

Thomas Kränzler

Klaus Broichhausen

Sven Hiller

Markus Waltemathe

J&uuml;rgen Steinwandel

Philipp Thuemmler

Matthias Schmidt

Martin Stroeer

Stefan Mueller

Jens Wittmer

Sven-Juergen Hiller

Philipp Thümmler

Rainer Willneff

Carsten Butz

Mark Geisel

Stefan Sasse

Sven-J Hiller

Hans-Christian Melzer

Wilhelm Meir

Stefan Laure

Karsten Gold

Josef Waermann

Bernd Stimper

Wolfgang Werner

Jochen Laun

Harald Geiger

Eggert Reese

Eberhard Knodel

Mihaela-Sorina Seitz

J&ouml;rg H&ouml;schele

Friedrich Oeffinger

Al&eacute;xander Sagel

Philip Betz

Rolf Reiter

Alexander Winkler

Marcin Olbrich

Hans Banhirl

Robert Axtner

Christoph Ader

Matija Burger

Michael Lahres

Martin Ströer

Walter Rothammel

Stephen Hoffmann-Ivy

Henri Wagner

Michael Mücke

Horst Pillhöfer

Stefan Müller

Stefan Neuhäusler

Sven-Jürgen Hiller

Jürgen Kraus

Markus Eisen

Manuel H Hertter

The invention relates to a method for the layered manufacturing of a structural component from powder, comprising the following steps: establishing at least one parameter (t) of a depression () in a produced layer () of the structural component; smoothing out the depression () if the at least one parameter (t) exceeds a predetermined value; and filling the smoothed-out depression () with powder ().

Method for the layered manufacturing of a structural component and device

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

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

A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine. In the axial direction, the respective axial bounding wall having the cooling-air outlet orifices has a layer-type structure; the cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer.

Cooling-air supply device for a gas turbine

A method for producing a component of a turbomachine is disclosed. The method includes a) layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone, where the deposition takes place in accordance with layer information of the component to be produced; b) local layer-by-layer fusion or sintering of the powder component material by energy supplied in the region of the buildup and joining zone, where the buildup and joining zone is heated to a temperature just below a melting point of the powder component material; c) layer-by-layer lowering of the component platform by a predefined layer thickness; and d) repetition of steps a) to c) until the component is finished. A device for producing a component of a turbomachine is also disclosed.

Method and device for producing a component of a turbomachine

A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating.

Method for producing a run-in coating, a run-in system, a turbomachine, as well as a guide vane

A method for electrochemically processing a workpiece surface using an electrode, which has at least one effective surface for processing the workpiece surface, and using an electrolyte, wherein the electrolyte is suctioned away from the effective surface. The invention further relates to an electrode, which has at least one electrolyte feed for supplying the electrolyte to the effective area and an electrolyte suctioning system for suctioning the electrolyte away from the effective area.

Method and electrode for electrochemically processing a workpiece

The invention relates to a process for producing an insulation element (), which can be arranged radially above at least one guide vane () in a housing () of a thermal gas turbine. The insulation element () is produced from a solid body () provided with a metallic shell (), the solid body () consisting at least partially of a ceramic material. The invention also relates to an insulation element (), which can be arranged radially above at least one guide vane () in a housing () of a thermal gas turbine, and to an aero engine having a housing (), in which at least one insulation element () is arranged radially above at least one guide vane ().

Method of producing an insulation element and insulation element for a housing of an aero engine

Disclosed is a coating for protecting a component against high temperatures and aggressive media, which coating has at least one subregion whose main constituent is chromium. The layer additionally comprises aluminum, the chromium content at least in the subregion in which chromium is the main constituent being greater than 30% by weight and the aluminum content being greater than or equal to 5% by weight. The invention further provides a process for producing such a coating, comprising chromizing the surface to be coated and subsequently alitizing the chromium-rich layer produced during chromizing.

Duplex-phase CrAl coating for improved corrosion/oxidation protection

Disclosed are a turbomachine having at least one radial gap seal which has at least two opposite ceramic coatings which are constructed in each case from a ceramic powder, the particle size of which is smaller than 1.0 &#x3bc;m, and a turbomachine having at least one radial gap seal, wherein the coatings are built up from powder-based individual layers, the outer layer of which has a higher ceramic fraction than a base layer close to the rotor or stator section respectively, wherein the particle size of the powder material is smaller than 1.0 &#x3bc;m.

Turbomachine

The invention relates to a bearing cage of a bearing means, in particular a ball or roller bearing, which is produced by means of a generative manufacturing method and has an outer flange and a bearing seat, which are joined together via a plurality of spring beams.

Bearing cage and bearing means having this type of bearing cage as well as method for designing, repairing and/or replacing such a bearing cage

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 sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed.

Seal assembly, method and turbomachine

The invention relates to a method for producing and repairing a part comprising at least two joined metal components, especially components of a gas turbine. In said method, corresponding joining surfaces of the components are joined together and connected by means of a pressure welding process, a machining allowance in the area of a joining zone of the two joining surfaces is upset during the joining process, and once the two components have been joined together, the machining allowance is machined by means of a precise electrochemical machining (PECM) process until a predefined final contour of the part has been obtained. The invention further relates to a gas turbine part obtained by means of the disclosed method.

Method for producing and repairing a part, and part of a gas turbine

A method for removing material from a component that is connected as an anode is disclosed. In an embodiment, an electrode that is connected as a cathode is guided to the component such that a gap is formed, an electrolyte is introduced into the gap, and a closed system is formed for the electrolyte by the formation of a duct. The electrolyte is continuously guided from an inlet opening to an outlet opening of the duct. Forming the duct, e.g., by guide elements that are mounted on the electrode, ensures that only those surface parts of the component to be machined from which material is to be removed enter in contact with the electrolyte while the other surface parts do not enter in contact with the electrolyte. Since the electrolyte is continuously guided across the surface, used electrolyte is continuously discharged along with residual matter while fresh electrolyte is delivered.

Method for removing material from a component, and electrode

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Dachau, Germany

Erwin Bayer