Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Other

Mtu Motoren-Und Turbinen-Union Munchen Gmbh

Mtu Motoren-Und Turbinen-Union Muenchen, Gmbh

Inno-Shape Gmbh

Karl-Hermann Richter

Herbert Hanrieder

Andreas Hartung

Erwin Bayer

Werner Humhauser

Joachim Bamberg

Ulrich Knott

Markus Schlemmer

Bernd Daniels

Josef Reischl

Klaus Breitschwerdt

Hans Juergen Schmuhl

Karlheinz Manier

Siegfried Boettcher

Reinhold Meier

Peter Hildebrand

Martin Reisacher

Michael Kuhl

Manfred Schill

Michael Strasser

Sonja Dudziak

Dieter Schneefeld

Marcus Klemm

Steffen Gerloff

Klaus Emiljanow

Bernd Stimper

Thilo Schmitt

Albert Grueninger

Christoph Ader

Christoph Over

Michael Weiß

Piotr Kowalczyk

Michael Weiss

Thomas Göhler

Albert GRÜNINGER

The present invention relates to an impulse body module group with at least two impulse body modules, which, in particular, are identical in construction, for a gas turbine blade, wherein each of the impulse body modules comprises a housing, which, in particular, is of one piece and which has a first cavity, which is closed, in particular in an airtight manner, by a first cover, which is joined to the housing, in particular in a material-bonded manner, and in which a single, in particular spherical or cylindrical, first impulse body is accommodated with play of movement in at least one first direction of impact, wherein the housing has no additional cavity or a single additional cavity, in which a single, in particular spherical or cylindrical, additional impulse body is accommodated with play of movement in at least one direction of impact.

Gas turbine blade impulse body module

A guide vane segment for a turbomachine stage that has an inner ring segment () and a plurality of guide vanes () that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge () of at least one guide vane (), in particular of at least 50% of the guide vanes (), axially toward a leading edge () of the guide vane () over at most 50% of a width (B) of the inner ring segment () and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (), at and/or in which at least one cavity () is configured which contains at least one impulse element () with clearance of motion for providing impact contacts.

Guide vane segment

The invention relates to a method for producing a low-pressure turbine blade from a TiAl material by means of a selective laser melting process, wherein during production in the selective laser melting process the already partially manufactured low-pressure turbine blade is preheated by inductive heating, and wherein the selective laser melting process is carried out under protective gas, the protective gas atmosphere containing contaminants of oxygen, nitrogen, and water vapor in each case of less than or equal to 10 ppm.

Method for producing low-pressure turbine blades from TiAl

The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank, manufacturing a housing element, producing an assembly opening corresponding to the housing element in the housing blank, arranging the housing element in the assembly opening, and joining the housing element to the housing blank by means of a welding method. In addition, the invention relates to a turbomachine housing.

Method for manufacturing a housing of a turbomachine and turbomachine housing

Disclosed is a method for producing a blade comprising a blade airfoil and a blade root for a turbomachine. The method comprises providing a first workpiece based on a first material and a second workpiece based on a second material which is different from the first material and has a higher temperature resistance than the first material; and connecting the first workpiece and the second workpiece by friction welding to form a composite component having a first region of the first material, and a second region of the second material. Optionally upon material-subtracting further processing, the first region forms the blade root, and the second region forms the blade airfoil.

Method for producing a blade for a turbomachine

A guide vane segment for a turbomachine stage that has an inner ring segment () and a plurality of guide vanes (-) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face () of the inner ring segment to an inner guide vane () that is circumferentially adjacent to an outermost guide vane () adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face () of the inner ring segment, at least one cavity () is configured which contains at least one impulse element () with clearance of motion for providing impact contacts.

A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber () in which at least one impulse element () is disposed with play, at least one second impact chamber () whose volumetric centroid is offset from a volumetric centroid of the first impact chamber () along a first matrix axis (A) and in which at least one impulse element () is disposed with play, and at least one third impact chamber () whose volumetric centroid is offset from the volumetric centroid of the first impact chamber () along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element () is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60&#xb0; and no more than 120&#xb0; is provided.

Turbomachine blade

The invention relates to a turbomachine including: a guide baffle, whose sguide blades are situated on c guide blade carriers; and an adjacent moving baffle including smoving blades; the guide baffle nincluding impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nincluding impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient of sum of the masses of all impulse bodies of the guide baffle divided by the difference (s&#x2212;c) of the number sof all guide blades minus the number c of all guide blade carriers amounts to at least 1.5 times quotient of sum of the masses of all impulse bodies of the moving baffle divided by the number sof all moving blades 

Turbomachine stage

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

The present invention provides a method for connecting a turbine blade or vane to a turbine disk or to a turbine ring. First, a connecting body is formed on the turbine blade or vane by supplying an additive suitable for fusion welding to a surface of the turbine blade or vane, melting the additive on the surface, with incipient melting of the surface, and allowing the additive and the surface to solidify. Then, the connecting body is connected to the turbine disk or to the turbine ring by means of a fusion welding process.

Method for connecting a turbine blade or vane to a turbine disc or a turbine ring

A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material.

Armoring sealing fins of TiAl vanes by induction brazing hard-material particles

Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising:

Process for producing a TiAl guide vane ring for a gas turbine and a corresponding guide vane ring

A method for depositing material layers on a workpiece made of a material which contains a titanium aluminide includes the steps of: preparing the workpiece; heating the workpiece in a localized region by induction to a predefined preheating temperature; and depositing an additive, preferably in powder form, on the heated surface of the workpiece by build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding; the additive including a titanium aluminide.

Process and apparatus for applying layers of material to a workpiece made of tiAl

A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.

Method for hardfacing the Z-notch of tial blades

A blade-disk unit for a turbine engine includes a disk and a plurality of blades which are integrally connected to the disk, a welding seam being disposed in the joining region between the blade and the disk, which welding seam is situated entirely either in the blade or in the disk.

Growing community of inventors

Markt Indersdorf, Germany

Karl-Hermann Richter