Mtu Aero Engines Ag

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Mtu Aero Engines Gmbh

Motoren- Und Turbinen-union Munchen Gmbh

Siegfried Sikorski

Michael Schober

Reinhold Schoenacher

Thomas Hess

Wilhelm Satzger

Karl-Heinz Dusel

Hans-Christian Melzer

Axel Rossman

Erwin Bayer

Axel Rossmann

Andreas Jakimov

Werner Huther

Manuel Hertter

Gerhard Wydra

Werner Huether

Bertram Kopperger

Wolfgang Krueger

Franz Puchinger

Wilhelm Meir

Klaus Broichhausen

Markus Waltemathe

Axel Mattschas

Josef Waermann

Wolfgang Diepolder

Benedikt Albert

Reinhold Sch&ouml;nacher

Robert Bader

Siegfried Schmid

Josef WÄRMANN

Wilhelm Meier

Stefan Neuhäusler

A rotor blade airfoil () for a turbomachine () that is adapted for rotation about a longitudinal axis () of the turbomachine () is provided. The rotor blade airfoil () is built from an airfoil material reinforced with a fibrous material (). At least a portion of the fibers of the fibrous material (), in particular at least 20%, preferably at least 30% of the fibers, are oriented in a first fiber direction (), and the first fiber direction () is tilted with respect to the stacking axis of the rotor blade airfoil ().

Rotor blade airfoil for a turbomachine

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 present invention relates to a process for producing a seal arrangement () for a turbomachine which comprises a seal support () and a stripping lining () which is arranged on the seal support, wherein the seal support comprises a fiber-reinforced plastic and the stripping lining comprises polysiloxane, and wherein the seal support and the stripping lining are prepared in a non-cured state and are arranged in direct contact with one another in accordance with the configuration of the seal arrangement, and are subsequently subjected to a common curing process such that fiber-reinforced plastic and polysiloxane cross-link with one another. The present invention further relates to a correspondingly produced seal arrangement and to a turbomachine having such a seal arrangement.

Seal arrangement for a turbomachine and process for the production thereof

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

A composite laminate or layer structure includes a substrate ( ) and a cover layer ( ) bonded thereon. The substrate is made up of at least one layer ( ) of fiber-reinforced synthetic material. The cover layer includes at least one layer ( ) of metal fibers and/or threads ( ), and a metal sheet ( ) forming the outer surface skin ( ) of the layer structure. The metal sheet is bonded by soldering or sintering onto the metal fibers and/or threads ( ), while the layer of metal fibers and/or threads in turn is bonded to the underlying fiber-reinforced synthetic material ( ) by being mutually and integrally permeated by a synthetic resin matrix and bonding material. Also, the metal fibers and/or threads ( ) may be intermeshed with the fibers of the synthetic material ( ). To provide improved bonding at both opposite sides thereof, the layer ( ) of metal fibers and/or threads ( ) has a lower porosity on the side adjoining the metal sheet, and a higher porosity on the side adjoining the fiber-reinforced synthetic material ( ) of the substrate.

Layer structure including metallic cover layer and fiber-reinforced composite substrate, and a method of making the same

A rotor for a propulsion plant has hybrid rotor blades arranged circumferentially around and extending essentially radially from a rotor. To reduce vibrations, the rotor blade has a metallic blade root and each blade has a metallic blade section that forms at least a portion of the blade leading edge and the area of the blade surface adjacent to the blade leading edge, and a blade section made of fiber-reinforced synthetic material or composite material. The blade sections ( ) of each blade ( ) are so correlated to each other that damage or loss of the composite material blade section ( ) still enables the propulsion plant to deliver a required emergency power.

Rotor with integrated blading

The invention relates to a composite material having a substrate, which contains at least one fiber layer, and a cover layer, which adjoins the substrate and which, at least adjacent to the at least one fiber layer, contains metallic fibers and/or threads. The at least one fiber layer of the substrate and the metallic fibers and/or threads of the cover layer being saturated with binder and, as a result, the substrate and the cover layer are formed together or connected. Metallic, ceramic or glass-type particles are embedded in the cover layer in the area of the metallic fibers and/or threads. Preferably, the particles may be one or more or a combination of TiC, TiN, TiAl, Fe, steel, Ni, Si, metal alloys, diamond, or glass. In addition, the invention provides a process for manufacturing a composite material and articles of manufacture comprising the composite material, especially for rotor blades or propellers. The composite material and products comprising it display improved abrasion and erosion resistance and are protected from electrical damages.

Composite material and process for manufacturing same

A blade for a fluid flow machine such as a jet turbine engine includes a blade body (2) that is to be exposed to the fluid flow and therefore is subject to damage by erosion due to abrasive particle entrained in the fluid flow and due to thermal loading. The blade body (2) is a layered body including base layers (6) of a fiber reinforced synthetic material and a metallic cover layer (7) applied as an erosion protective layer onto at least a portion or the entirety of the surface of the base layers (6). The cover layer (7) includes metallic fibers or threads (9A, 9B) which are bonded with the fiber reinforced synthetic material of the adjacent base layers (6) by the same synthetic resin binder material permeating through and forming a matrix for all the layers (6 and 7). The metallic fibers or threads (9A, 9B) embedded in a synthetic resin matrix are characterized by a high degree of erosion resistance and a good tolerance for defects in the case of local impact or erosion damage. The blade may be a blade of a fan or compressor stage of a jet turbine engine. A method for manufacturing and a method for repairing such blades involves exposing outer layers of fibers of a blade, and applying thereon a cover layer of metallic fibers or threads. An additional outer protective layer may be applied on the cover layer.

Blade for fluid flow engine having a metallic coating layer, and method

A structural component which consists of a fiber-reinforced, composite material is provided with a protective coating against erosion. The protective coating includes an adhesion-promoting, intermediate layer on the component, an electrically insulating baked, inorganic lacquer layer for protection against erosion and an electrically conducting covering layer, for protection against lightning strikes. The covering layer consists of a baked and compressed inorganic lacquer and the lacquer of the lacquer layer and of the covering layer is baked on the component below the temperature which causes damage to the structural component or below the softening or decomposition temperature of the component. The protective layer is advantageously used for the external components of propulsion units, such as housings, nose cones or fan blades.

Carbon fiber-reinforced composite material with a layer which provides

A vibration damper for rotor housings includes a rubber-elastic damping band (6) that encircles the outer circumference of the rotor housing (4) in a contour fitting manner. A clamping band (7) encircles the damping band (6) and secures the damping band to the housing (4). The clamping band is made of a material having a different modulus of elasticity than the material of the rotor housing, which achieves a detuning of the vibrational system including the rotor housing and the vibration damper as components. Such a detuning reduces the vibrational tendency of the rotor housing. Frictional rubbing between the damping band and the housing surface, and between the damping band and the clamping band effectively damps or dissipates the energy of any vibration that does occur. The clamping band includes a tension adjustment element that is adjustable and releasable so that the clamping band and the entire vibration damper may easily be removed from the housing for carrying out maintenance and inspection procedures.

Vibration damper for rotor housings

A guide vane for an axial guide baffle of an axial flow engine, such as a jet engine, is adjustable in its position about a guide vane adjustment axis extending radially to a rotational engine axis. The guide vane has a vane body and an adjustment lever extending at an angle of about 90.degree. away from the adjustment axis. The vane body, the adjustment lever, and at least one bearing journal form an integral one piece construction either of molded fiber composite material or of forged, e.g. drop forged, metal.

Adjustable guide vane for turbines, compressors, or the like

A protective sheet for a resin pre-impregnated fiber board (prepreg) incorporates ferromagnetic material. This permits effective and safe manipulation of the fiber board during processing (trimming) and in the manufacture of fiber components.

Composite comprising a resin prepreg and a protective sheet containing

A propeller for a prop-jet engine having a propellor blade formed as a hollow shell member whose outer surface has an aerodynamic blade profile, the propellor blade being secured to a rotor via an adjustment pin. The hollow shell member is internally braced partly along its radial length by a flexible spar secured to the pin and made of thermoplastic material. The flexible spar is hollow and receives a metal spar hich is fixed to the pin and is given flexibility in bending by the provision of a slot therein.

Deflectable blade assembly for a prop-jet engine and associated method

An anti-rupture ring is slit axially at least at one location and is provided thereat with clamping devices which permit a rapid tightening and loosening of the anti-rupture ring. In one embodiment, the clamping of the anti-rupture ring can be varied hydraulically so as to minimize clearance losses in operation. The invention can be used in all types of turbo engines endangered by breakage of rotor blades, particularly in aircraft gas turbine construction, and it permits simple, damage-free mounting and a well-defined clamping of the anti-rupture ring.

Growing community of inventors

Munich, Germany

Siegfried Sikorski