Abstract: In a method for surface blasting hollow spaces or cavities, especially cavities of gas turbines, shot balls are accelerated with the aid of at least one vibrator, whereby the ultrasonically accelerated shot balls are directed onto surfaces of a cavity that is to be blasted. The vibrator is preferably positioned with a small spacing distance, preferably on the order of magnitude of the diameter of the shot balls utilized for the blasting, from the cavity to be blasted.
Type:
Grant
Filed:
December 7, 2005
Date of Patent:
January 12, 2010
Assignees:
MTU Aero Engines GmbH, Sonats
Inventors:
Stephen Hoffmann-Ivy, Patrick Cheppe, Jean-Michel Duchazeaubeneix, Erwin Bayer
Abstract: A brush seal has a bristle housing formed by a cover element and a support element. A plurality of bristles, which are wound around a core element and secured to the core element by a clamping element are positioned in the bristle housing. At least one of the support element and the cover element of the bristle housing are made of plastic.
Type:
Grant
Filed:
August 17, 2004
Date of Patent:
January 12, 2010
Assignee:
MTU Aero Engines GmbH
Inventors:
Stefan Beichl, Alfons Gail, Thomas Huppertz
Abstract: In a method for coating a substrate, and a coated object, in a first step, in an external current-less or electrolytic manner, nickel and/or cobalt and/or platinum are deposited on a substrate in a deposition bath. In the deposition bath, particles are additionally suspended which contain at least one metal selected from Mg, Al, Ti, Zn and no Cr, the particles becoming occluded in the coating. In a second step, the actual protective layer is produced by heat treatment. The coating of component parts may be used for aircraft turbines or gas turbines or for garbage incineration systems having temperature-resistant protective layers against high temperature corrosion.
Type:
Grant
Filed:
November 3, 2003
Date of Patent:
January 5, 2010
Assignee:
MTU Aero Engines GmbH
Inventors:
Andreas Dietz, Gebhard Klumpp, Juergen Olfe
Abstract: Pulsed laser drilling is used to produce bore holes having a small diameter, for example, in hollow workpieces. Turbine blades, e.g., have a multitude of fine cooling air bore holes, which are able to be produced by this method, e.g., with high positional accuracy and in an automated manner. A checking method is provided by which drilling faults, e.g., with regard to piercing and bore-hole geometry, may be detected in a more reliable manner. A method is for checking a bore hole introduced in a workpiece by laser pulses, in which characteristic signals from the area of the bore hole are received with the aid of a sensor and compared to setpoint values and only signals received in a characteristic time interval following a laser pulse are taken into account.
Type:
Grant
Filed:
October 23, 2004
Date of Patent:
December 29, 2009
Assignee:
MTU Aero Engines GmbH
Inventors:
Erwin Bayer, Mark Geisel, Thomas Herzinger
Abstract: A sealing arrangement, especially for a flow engine, for non-hermetically sealing a gap (12) between a rotor (10) and a stator (11), which comprises a seal having a plurality of sealing elements that are fixed to a sealing element support, said sealing element support being at least partially disposed in a receptacle (16) which is defined by a supporting element (17) and a cover element (18) is disclosed. The sealing element support is configured as a ring that is interrupted once or several times. Free ends (19, 20) of the sealing element support overlap in the area of interruptions in the circumferential direction. The contours of the supporting element (17) and the cover element (18) are adapted to the contours of the sealing element support and the sealing elements (15). At least one end (19, 20) of every part of the sealing element support is associated with an antirotation device (21, 22).
Abstract: An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.
Abstract: 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.
Abstract: A guide blade segment of a gas turbine, having at least one guide blade and having an inner cover band assigned to the radially inner end of the or each guide blade, is disclosed. An integral constituent part of the inner cover band of the guide blade segment is a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
Type:
Application
Filed:
January 19, 2007
Publication date:
December 10, 2009
Applicant:
MTU Aero Engines GmbH
Inventors:
Reinhold Meier, Claus Mueller, Karl-Heinz Dusel, Roland Huttner
Abstract: A method and a device for joining at least one rotor blade or at least one part of a rotor blade with a rotor support of a gas turbine, in particular a rotor blade connection of the rotor support, is disclosed. Corresponding connecting surfaces of the rotor blade, the rotor blade part, the rotor support or the rotor blade connection of the rotor support are joined by inductive high-frequency pressure welding. In this case, at least one rotor blade or rotor blade part is automatically supplied from at least one rotor blade reservoir and/or rotor blade part reservoir and, in addition, the rotor support is automatically positioned in such a way that the connecting surfaces to be joined are positioned precisely with respect to one another for the joining process.
Type:
Application
Filed:
March 14, 2007
Publication date:
December 10, 2009
Applicant:
MTU Aero Engines GmbH
Inventors:
Herbert Hanrieder, Alexander Gindorf, Reinhold Meier
Abstract: In a transverse flux machine, the rotor has multiple permanent magnet rings that are arranged axially in proximity to one another. The stator surrounds the rotor concentrically in at least some sections, forming an air gap. The stator has multiple stator coils oriented coaxially with the permanent magnet rings and the stator coil has two terminals. An active reactive power source to be controlled has two terminals for each stator coil, the respective stator coil being connected to each. In the event of a fault incident in one of the stator coils, a monitoring arrangement supplies triggering signals for the active reactive power source so that the two terminals of the respective stator coil are interconnected with a low resistance.
Type:
Grant
Filed:
April 28, 2006
Date of Patent:
December 8, 2009
Assignee:
MTU Aero Engines GmbH
Inventors:
Andreas Gruendel, Hubert Herrmann, Bernhard Hoffmann
Abstract: A device is provided for displacing gas turbines, especially during maintenance thereof. The device comprises several transporter platforms which are arranged behind each other. At least one gas turbine can be positioned on each of the transporter platforms. The or each gas turbine can be displaced by displacing the transporter platforms.
Abstract: A thermal barrier layer for metallic components, in particular for gas turbine components which are subject to high temperatures or hot gas, is disclosed. The thermal barrier layer includes an inner contact layer and an outer top layer, where the inner contact layer is applied to a surface of the component via an adhesion-promoting layer that is disposed therebetween, and between the outer top layer and the inner contact layer an intermediate layer is formed.
Type:
Application
Filed:
June 12, 2007
Publication date:
December 3, 2009
Applicant:
MTU Aero Engines GmbH
Inventors:
Stefan Schneiderbanger, Ralf Stolle, Thomas Uihlein, Wolfgang Wachter
Abstract: A process for connecting metallic structural elements, in particular structural elements of a gas turbine, and a component made by the process, is disclosed. The connecting of corresponding connecting surfaces of the structural elements is performed by inductive high-frequency pressure welding and the structural elements consist of different or similar metallic materials with different permeabilities and/or thermal conductivities. During the inductive high-frequency pressure welding, at least one process-specific parameter is controlled in such a way that at least the connecting surfaces are respectively heated essentially simultaneously up to at least near the respective melting point of the metallic materials.
Abstract: A method and apparatus for surface hardening parts is disclosed. To harden a surface of a part, a relative movement, or advancing motion, is established between the part and at least one sonotrode-like tool which is excited in the ultrasonic frequency range. The tool is aligned during the surface hardening in such a way to the surface of the part to be hardened that a tool axis running in the effective direction of the tool runs at an angle to the surface of the part to be hardened.
Type:
Application
Filed:
November 24, 2005
Publication date:
November 12, 2009
Applicant:
MTU Aero Engines Gmbh
Inventors:
Joachim Bamberg, Roland Hessert, Wilhelm Satzger
Abstract: An engine control system is provided having a control unit and a monitoring module. The monitoring module, together with the control unit, forms one structural unit and is designed as a detachable module having an independent electromagnetic shielding.
Type:
Application
Filed:
May 7, 2008
Publication date:
November 5, 2009
Applicant:
MTU Aero Engines GmbH
Inventors:
Armin Geissler, Thomas Goeler, Werner Riebesel
Abstract: A component, specifically a component for a gas turbine, having a main body of a base material and a wear protection coating applied to a surface of the main body, specifically a protective coating against corrosion and/or oxidation and/or erosion, is disclosed. A barrier coat is applied between the main body and the wear protection coating to protect the main body during chemical or electrochemical decoating of the component.
Type:
Application
Filed:
March 3, 2006
Publication date:
October 29, 2009
Applicant:
MTU Aero Engines GmbH
Inventors:
Wolfgang Eichmann, Falko Heutling, Karl-Heinz Manier, Markus Uecker, Thomas Uihlein
Abstract: A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.
Type:
Application
Filed:
February 28, 2005
Publication date:
October 22, 2009
Applicant:
MTU Aero Engines GmbH
Inventors:
Manfred A. Daeubler, Horst Mueller-Wittek, Renate Mendritzki, Ulrike Hain, Werner Humhauser
Abstract: A turbocompressor flow structure comprises a ring chamber which is arranged concentrically to an axis of a turbocompressor in an area of free blade/vane ends of a rotor blade ring/vane ring and is adjacent radially to a main flow channel. A ring chamber is provided which is bordered by a front upstream wall, a rear downstream wall and a wall that runs essentially axially. Baffle elements are arranged in the ring chamber and the ring chamber permits flow penetration in a circumferential direction in a front and/or rear area. At least one opening is provided in the area of the wall that runs essentially axially or in the area of the upstream wall and permits flow penetration out of the ring chamber, at least one compressor chamber being provided to accommodate this outgoing flow.
Abstract: A method and a measuring system for characterizing a deviation of an actual dimension of a component from a nominal dimension of the component, is disclosed. In an embodiment, the method includes a) determining at least one measured value characterizing the actual dimension at a position of the component by a measuring device; b) making a nominal value available with which the nominal dimension is characterized as a function of the position of the measured value; c) determining a spatial distance between the measured value and the nominal value; d) making a limiting criterion available with which a permissible deviation from the nominal value is characterized as a function of the position of the measured value; and e) determining a tolerance utilization value characterizing the deviation for the measured value as a function of the spatial distance and of the limiting criterion.
Abstract: A device and a method are disclosed for visualizing positions on a surface by means of a marking which is produced by an optically detectable radiation. In order to permit a residue-free marking which can be observed with a camera from partly extremely oblique observation directions, the device has an optical waveguide, which is coupled to a radiation source and whose light output region can be located at a desired position of the surface in order to emit optically detectable radiation at the desired position of the surface through the optical waveguide. As a result, the radiation is emitted at the desired position of the surface in various spatial directions.