Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Mtu Aero Engines Ag

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Aero Engines Gmbh

Michael Schober

Siegfried Sikorski

Reinhold Schoenacher

Thomas Uihlein

Heinrich Walter

Michael Strasser

Ralf Stolle

Axel Mattschas

Wolfgang Diepolder

Robert Bader

Andreas Kaehny

Siegfried Schmid

Josef Lachner

Werner Moosrainer

Reinhold Sch&ouml;nacher

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

A method and device for partially masking a component or assembly during a coating process, the device including at least one masking plate for separating a region to be coated from a region to be masked, the masking plate having at least a portion of at least one opening which conforms closely to the contour of the component and is adapted to allow passage of the component therethrough is provided. In masked region, a gap is present along opening, at least one sealing element being disposed at the gap on the side of the masked region.

Device and method for partially masking a component zone of a component

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

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 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.

Growing community of inventors

Munich, Germany

Michael Schober