Mtu Aero Engines Gmbh

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Other

Mtu Aero Engines Ag

Reinhold Meier

Karl-Hermann Richter

Martin Thoma

Herbert Hanrieder

Roland Huttner

Karl-Heinz Dusel

Erich Steinhardt

Karel Mazac

Alexander Gindorf

Wilfried Schuette

Ludwig Schaller

Bernd Stimper

Georg Moosrainer

Erhard Schittenhelm

Anton Albrecht

Thilo Schmitt

Karl Kerger-Knilling

Wilfried Sch&uuml;tte

Mario Schmidt

Claus MÜLLER

A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements.

Component and method for joining metal elements

Disclosed is a honeycomb structure for non-hermetic rotor-stator and rotor-rotor seals in turbo machines. Said honeycomb structure comprises a plurality of at least predominantly radially oriented honeycomb cells which are separated by cell walls, are open on one side, cooperate with at least one sharp sealing edge that rotates relative to the honeycomb structure, and can yield relative to the sharp sealing edge by being deformed and/or material being removed therefrom when being touched. The walls of the honeycomb cells have holes according to a defined perforation pattern.

Honeycomb structure

A process for manufacturing a honeycomb seal is disclosed. The process includes the following steps: a) the honeycomb structure is brought to the desired three-dimensional form and is fixed in this form; b) then the honeycomb structure is filled with a filler material; c) then the honeycomb structure filled with the filler material is machined on a side on which a carrier element is arranged, such that this side has the desired contour and that the end edges of the honeycomb structure are sealed flushly with the filler compound; d) then the side contoured in this way is coated with a coating; e) next the carrier element is applied to the coating, preferably by laser powder build-up welding.

Process for manufacturing a honeycomb seal

In a method of repairing a structural component, especially a stator-side structural component such as a housing or a guide vane ring of a gas turbine, a damaged section is separated-out along a separating line and removed from the structural component, and a new section that replaces the removed damaged section is connected with the structural component by welding along the separating line to produce a weld seam. The damaged section is separated-out from the structural component so as to minimize the length of the separating line and thus the weld seam. Depending on the material thickness distribution of the component along the separating line, material is removed from the structural component to provide the most uniform possible material thickness along the weld seam. After connecting the new section with the structural component by welding, at least the removed material is renewed by laser powder deposit welding.

Method for repairing or manufacturing a component

A method for producing gas turbine components, in particular blades, blade sections or rotors with integral blades for a jet engine is provided. The method comprises at least the following steps: preparation of at least one metallic powder and at least one expanding agent; mixing of the metallic powder or each metallic powder with the expanding agent or each expanding agent; compression of the resultant mixture to form at least one semi-finished product; expansion of the semi-finished product or each semi-finished product by heating to achieve a defined degree of expansion; termination of the expansion process by cooling, once the defined degree of expansion has been reached.

Method for producing gas turbine components

The present technology relates to the problem that during diverse machining steps of application to the production or reconditioning of internally cooled gas turbine blades, an undesired effect may be had on sections of the gas turbine blades and proposes, as an improvement, to inject the cavity of the gas turbine blades before the machining steps with a plastic material which can be removed without trace, such as polystyrene, which can be subsequently removed again, in particular by heat.

Gas turbine components and method for machining gas turbine components

A static gas turbine component, especially for an aircraft engine, is formed at least partially region-wise of metal foam. An abradable shroud lining of metal foam and a carrier allow a radial through-flow of gas.

Gas turbine component

A method is provided for joining blades to blade roots or rotor disks when manufacturing and/or repairing gas turbine blades or integrally bladed gas turbine rotors. A blade and a blade root or rotor disk that is to be joined to the blade are supplied, and provided with a thickening in sections that are to be joined together. The sections of the blade and the blade root or rotor disk that are to be joined together are machined so as to form recesses and; c) are then aligned relative to each other, opposite recesses defining at least one groove-shaped seam preparation. The blade and the blade root or rotor disk are joined in the area of the or each seam preparation by means of laser power build-up welding and the joined blade and blade root or rotor disk are machined so as to provide a gas turbine blade or an integrally bladed gas turbine rotor having a predefined geometrical profile.

Method for joining blades to blade roots or rotor disks when manufacturing and/or repairing gas turbine blades or integrally bladed gas turbine rotors

A milling tool which is used to mill recesses, in particular, circular-shaped grooves, in a workpiece is provided. The milling tool () is disposed on a disk-shaped or plate-shaped base body () and on at least one cutting body () arranged on the outer periphery of the base body (). The cutting body or each cutting body () is inclined in relation to the disk-shaped base body or the plate-shaped base body ().

Milling tool and method for milling recesses

A method is available for repairing metallic components such as gas turbines, which have mechanically weight-carrying grooves, where the longitudinal edges of the grooves which exist on the component surface are largely in a plane and their actual contour deviates, at least locally, due to removal and/or displacement the component material from the desired contour. The method begins with abrasive blasting of the groove surfaces, followed by closing of the open groove ends by build-up welding, and subsequent filling of the grooves with soldering powder. The soldering powder is heated to liquefaction, then cooled and solidified in a vacuum, and the desired contour of the groove is then machined.

Method of repairing metallic components

The invention relates to a blade and a rotor for a gas turbine and to a method of joining blade parts of a gas turbine, a blade-body section ( ) and at least one further blade part ( ) being provided, and the blade-body section ( ) being provided with at least one end joining area ( ) and the further blade part ( ) being provided with an end joining area ( ), an inductor ( ) being arranged so as to be adjacent to the joining areas ( ) of the blade-body section ( ) and of the second blade part ( ), the joining areas ( ) of the blade-body section ( ) and of the further blade part ( ) being positioned essentially in alignment with and at a distance from one another, and the blade-body section ( ) and the second blade part ( ) being welded to one another by energizing the inductor ( ) with a high-frequency current and by bringing them together with their joining areas ( ) touching one another (FIG. 1).

Blade and rotor for a gas turbine and method for linking blade parts

A method is disclosed for reconditioning blades for turbo-machinery that have a material deficiency resulting from wear and tear, damage, or dimensions that are smaller than specified, in which material is removed, at least from parts of the blade, and is replaced with new material. The actual geometry of the blade is measured at certain specific points and is stored. The desired geometry, or the desired profile in its desired position, is determined via data processing technology. The desired geometry is compared with the actual geometry, and in cases of significant deviations in position, is adjusted to coincide with the actual geometry. The adjusted desired geometry is mathematically reduced by a defined amount of coating to be removed. The calculated net geometry is actually produced via the removal of material, at least over part of the blade, and new material is applied to the finished net geometry, until the desired profile is achieved.

Method for reconditioning blades

A method for repairing/manufacturing an integrally bladed rotor for a turbine or turbo engine, in which, in the case of a repair, at least one vane section to be replaced is removed leaving a stub section to which a replacement vane section is to be welded, and, in the case of manufacturing, a carrier to be provided with vanes has stubs projecting over its peripheral surface, to each of which a vane is to be welded, includes the steps of: arranging an inductor around the front face of the stub section or stub; positioning a replacement vane section or vane at a small radial distance from and aligned with the stub section or stub; and welding the replacement vane section or vane to the stub section or stub, respectively, in a protective gas atmosphere by exciting the inductor with high-frequency current and moving the opposing heated part surfaces together.

Method for repairing and producing integrally bladed rotors for a turbine or turbo engine

A form-fitting cast-on enclosure arrangement has parallel chucking surfaces for the fixing of metallic workpieces with irregular contours to be processed. A process is provided for the manufacturing and separating of the enclosure arrangement. The enclosure arrangement is made of plastic material and consists of several spaced ribs which are connected by webs. The enclosure arrangement has the advantage that workpieces with irregular contours can be enclosed in a cost-effective and fast manner and can be finished or repaired.

Enclosure arrangement for fixing workpieces to be processed and a process for manufacturing and separating the enclosure arrangement

A protective coating is applied on a local region of a surface of a component on which direct deposit of a uniform coating of protective material is impeded due to a complex shape of the region to be covered or inaccessibility or inability to apply a uniform deposition or electrical field therefor. The coating is formed by a foil having a solder backing layer with a thin layer of uniform thickness of the protective material electrolytically deposited on the backing layer, the foil being cut to size corresponding to an area of the local region of the component to be protected. The cut to size foil is positioned and held on the local region of the component to be protected; and fixed in place by melting the solder to fuse the foil to the component and cover the local region.

Growing community of inventors

Dorfen, Germany

Reinhold Meier