Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Mtu Motoren-und Turbinen-union Munchen Gmbh

Fraunhofer-gesellschaft Zur Foerderung Der Angewandten Forschung E.v.

Daimler-benz Ag

Joachim Bamberg

Roland Hessert

Wilhelm Satzger

Thomas Hess

Erwin Bayer

Peter Adam

Herbert Hanrieder

Axel Rossmann

Karl-Hermann Richter

Alexander Gindorf

Andreas Jakimov

Stefan Schneiderbanger

Wilfried Smarsly

Steffen Schlothauer

Manuel Hertter

Christian Liebl

Georg Schlick

Alexander Ladewig

Ludwig Steinhauser

Guenter Zenzinger

Karl-Heinz Dusel

Bertram Kopperger

Falko Heutling

Holger Polanetzki

Robert Schuster

Bernd Koehler

Martin Eckstein

Wolf-Dieter Feist

Philipp Doebber

Johannes Casper

Thomas Mack

Hans-Uwe Baron

Dietmar Helm

Klaus-Dieter Tartsch

Thomas Bautsch

Josef Mayr

Franz Heitmeir

Roland Höfling

Joerg Esslinger

Martin Barth

Martin BUßMANN

Bernd KÖHLER

Laura Bürger

Günter Zenzinger

Benjamin Henkel

Jörg Esslinger

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 method for manufacturing a brush seal with inclined bristles. In order to be able to manufacture these brush seals in an especially cost-effective manner, at least the following steps are provided: provision of a brush blank with at least one metal thread or wire packing fastened at or in at least one wire core; local, at least partial heating of at least the wire core and/or a subregion of the thread or wire packing adjacent to the wire core, by a current flow through the wire core; bending of the thread or wire packing relative to the wire core for producing of the inclined position of the bristles of the brush seal. The invention further relates to an apparatus for manufacturing brush seals and a brush seal for a turbomachine, in particular for an aircraft engine.

Method for manufacturing a brush seal with inclined bristle

The present invention relates to a device as well as a method for the additive manufacture of components by deposition of material layers by layer-by-layer joining of powder particles to one another and/or to an already produced pre-product or substrate, via selective interaction of the powder particles with a high-energy beam, wherein, for smoothing a surface of the component being produced running crosswise to the deposited material layers in between the deposition of two layers of the component, the complete edge region of the last layer that is applied and that runs along a surface of the component being produced is compacted in a direction of action that has a directional component parallel to the build-up direction of the layers, and/or at least one edge region of a surface of the component is also compacted.

Micro-forging by a generative manufacturing process

Disclosed is a method for generatively producing components by layer-by-layer building from a powder material by selective material bonding of powder particles by a high-energy beam. An eddy current testing is carried out concurrently with the material bonding. Also disclosed is an apparatus which is suitable for carrying out the method.

Control in generative production

Disclosed are a method for forming a thermal barrier layer for a metallic component, which method involves forming a ceramic coat in which at least in part aluminum oxide and titanium oxide are disposed, the aluminum oxide and the titanium oxide being introduced by infiltration of aluminum-containing and titanium-containing particles or substances or by physical vapor deposition.

CMAS-inert thermal barrier layer and method for producing the same

A method for the generative production of a component and a device for carrying out such a method, includes the following steps: applying a material layer with a constant layer thickness; solidifying a region of the material layer according to a component cross section; generating an eddy-current scan of the solidified region, a scan depth corresponding to a multiple of the layer thickness; determining a material characterization of the solidified region taking into consideration a previous eddy-current scan of solidified regions of lower-lying material layers; and repeating the steps until the component is assembled. An electric material characterization of each individual layer is determined using a recursive algorithm of individual measurements (monolayer by monolayer), and thus the entire component is tested step by step completely in a highly resolved manner.

Method and device for the generative production of a component

The invention relates to a method for the determination, at least in regions, of a contour of at least one additively manufactured component layer, in which a contour line of the component layer is traveled over, at least in regions, by a laser beam, and a time exposure of the traveled contour line is produced by a camera system. The invention further relates to a device for the determination, at least in regions, of a contour of at least one additively manufactured component layer. For this purpose, the device comprises at least one laser system, by which a contour line of the component layer can be traveled over, at least in regions, by a laser beam, and a camera system, which is designed to produce a time exposure of the contour line traveled over by the laser beam.

Method and device for determining a contour, at least in regions, of at least one additively manufactured component layer

A method for determining residual stresses of a component (), in particular a component of an aircraft engine, while it is being manufactured by an additive manufacturing process. The method includes the following steps: creating at least one local melt pool () in a surface () of the component () to be manufactured after a predetermined portion of the component is completed; optically detecting surface distortions and/or elongations occurring at least in a region around the created melt pool (); and determining the residual stresses of the component () which are present at least in the region around the created melt pool () based on the optically detected surface distortions and/or elongations. Further an apparatus for determining residual stresses of a component () while it is being manufactured by an additive manufacturing process is provided.

Method and apparatus for determining residual stresses of a component

The invention relates to a method and device for ascertaining an edge layer characteristic of a component (), in particular a component () for an aircraft engine. In the method, a reference body () with a known edge layer characteristic is arranged on the surface of the component (). An ultrasonic wave () is introduced into the surfaces of the component () and the reference object () by an ultrasonic transmitter (). An ultrasonic wave () resulting from the exchange between the component () and the reference body () is detected by an ultrasonic detector (), and an edge layer characteristic of the component () is ascertained by an ascertaining device () using a difference between the generated ultrasonic wave () and the resulting ultrasonic wave ().

Method and device for ascertaining an edge layer characteristic of a component

Disclosed is a method for the non-destructive testing of workpiece surfaces of a workpiece by means of fluorescent penetrant testing or dye penetrant testing. The method comprises applying a penetrant to the region of the workpiece surface to be examined, thereby allowing the penetrant to penetrate into possible recesses in the workpiece surface, applying a developer to the region of the workpiece surface to be tested; bleaching the penetrant by a gaseous or liquid oxidant; and visually assessing the penetrant that has remained in the recesses present in the workpiece surface.

Method for the non-destructive testing of workpiece surfaces

A method for coating a component, in particular a component of a gas turbine or of an aircraft engine, is disclosed. The coating is applied to the component by kinetic cold gas spraying, where prior to the deposition of the coating, the surface of the component to be coated is cleaned and compacted by shot peening with a blasting media. A component produced in this manner is also disclosed.

Coating method for forming crack-resistant coatings having good adherence and component coated in this manner

The invention relates to a method for joining two components () made of a metal material, which are connected on two mutually associated joining surfaces () by means of a joined connection, wherein at least one of the components () is strengthened in at least a partial region of the joining surface () thereof prior to joining. The invention further relates to a joined connection of two components () made of a metal material.

Method for joining and joined connection of two components made of a metal material

The invention relates to a method of nondestructive and contactless testing of components (), wherein ultrasonic waves () are irradiated onto the surface of the component () at a predefinable, non-perpendicular angle of incidence () using an ultrasonic transmission sound transducer () arranged spaced apart from the surface of the component () and the intensity of the ultrasonic waves () reflected from the surface of the component () is detected with time resolution and/or frequency resolution by the antenna array elements () of an ultrasonic antenna array () configured for detecting ultrasonic waves () and the phase shift of the ultrasonic waves guided at the surface of the test body is determined therefrom with respect to the ultrasonic waves () directly reflected at the surface of the component ().

Destruction-free and contactless inspection method and inspection apparatus for surfaces of components with ultrasound waves

A method for joining at least two components by inductive high-frequency pressure welding is disclosed. The first component has a first material structure with a first hardness and the second component has a second material structure with a second hardness which is smaller than the first hardness. Both components are inductively heated in the region of the joining surfaces and are subsequently pressed together by a compressive force. The joining surface of the first component with the first hardness, which is greater than the second hardness of the second component, is pre-contoured in a spherical, conical or convex manner prior to joining the two components.

Method for joining components

A method for nondestructive testing of workpiece surfaces by a fluorescent penetration test is disclosed. An embodiment of the method includes a) cleaning the area of the workpiece surface that is to be inspected; b) applying a fluorescent liquid penetrant to the area of the workpiece surface that is to be inspected, where the penetrant penetrates into possible recesses in the workpiece surface; c) removing the excess penetrant from the workpiece surface; d) applying a developer to the area of the workpiece surface that is to be inspected; e) bleaching the fluorescent penetrant by a beam of light in the layer formed by applying the developer to the workpiece surface; and f) visual evaluation of the fluorescent penetrant remaining in the recesses present in the workpiece surface.

Method for nondestructive testing of workpiece surfaces

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Dachau, Germany

Joachim Bamberg