Patents Assigned to MTU Aero Engines GmbH
  • Method for producing a component by calculating a load line of the component
    Patent number: 8951606
    Abstract: A method for producing a component is disclosed. The method includes calculating a load line of the component as a result of a load to be absorbed by the component and applying a layer on a core by gas dynamic cold spraying, where the layer has a layer section and where the layer section runs along the calculated load line.
    Type: Grant
    Filed: January 29, 2011
    Date of Patent: February 10, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Manuel H. Hertter, Andreas Jakimov, Marcin Olbrich, Mihaela-Sorina Seitz, Juergen Kraus, Bertram Kopperger, Klaus Broichhausen, Hans Banhirl, Erwin Bayer, Wolfgang Werner, Eberhard Knodel
  • Method for mounting an integral inner ring of a turbocompressor stator
    Patent number: 8943689
    Abstract: A method for mounting an integral inner ring (10) of a turbocompressor stator to a guide vane ring (12) comprises the following steps: -Providing the guide vane ring (12) with an inner radius S; -Providing inner ring (10) with an outer radius R, which corresponds to the inner radius S; -Pre-tensioning inner ring (10) to an outer radius r that is smaller than the outer radius R of the untensioned inner ring (10); and -Relaxing inner ring (10) to the outer radius R.
    Type: Grant
    Filed: January 14, 2010
    Date of Patent: February 3, 2015
    Assignee: MTU Aero Engines GmbH
    Inventor: Frank Stiehler
  • Replacement part for a gas turbine blade of a gas turbine, gas turbine blade and method for repairing a gas turbine blade
    Patent number: 8944772
    Abstract: A replacement part for a gas turbine blade is disclosed. The replacement part is designed to replace a removed portion of the blade, the portion including a section of the blade tip and a section of the leading edge and/or the trailing edge, and the replacement part having at least one joining side with which it can be brought to contact with the blade that is reduced by the removed portion and joined therewith. The joining side has at least one section, the cross-section of which is U-shaped.
    Type: Grant
    Filed: September 9, 2009
    Date of Patent: February 3, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Armin Eberlein, Albert-Valentin Schneider
  • Method and device for the surface peening of a partial element of a component of a gas turbine
    Patent number: 8943659
    Abstract: A method and device for the surface peening, especially ultrasonic shot-peening, of at least one partial element of a component of a gas turbine, is disclosed. The partial element, e.g., a sealing fin, and at least one surface of a vibration device impinging the blasting material are positioned relative to each other at an angle between 70° and 90° based on the direction of extension of the sealing fin.
    Type: Grant
    Filed: December 5, 2007
    Date of Patent: February 3, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Erwin Bayer, Max Niegl, Holger Polanetzki, Thomas Peschke, Thomas Dautl, Philipp Thuemmler
  • Method for the production of an integrally bladed rotor, and rotor
    Patent number: 8936442
    Abstract: A method for manufacturing an integrally bladed rotor (10), in particular for a gas turbine, including the following method steps: preparing a rotor base member (12) having at least one first weld surface (16) and one blade (14) having a second weld surface (18); positioning the rotor base member (12) and the blade (14) in such a way that a join zone (20) is formed between the first and second weld surface (16, 18); and filling the join zone (20) with metal powder (24) and the laser welding or electron beam welding of the metal powder (24). An integrally bladed rotor (10) has a join zone (20) between the rotor base member (12) and blades (14), the join zone (20) being filled with welded metal powder (24).
    Type: Grant
    Filed: January 30, 2010
    Date of Patent: January 20, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Thomas Uihlein, Erich Steinhardt
  • Device and method for the surface peening of a component of a gas turbine
    Patent number: 8931318
    Abstract: A device for surface-peening, especially for the ultrasound shot-peening of a component of a gas turbine, having at least one vibration means that comprises a surface that propels the peening material, and having a holding means with which a surface area of the component and the surface of the vibration means can be arranged with respect to each other is disclosed. In this context, the angular position of the surface of the at least one vibration means can be adjusted relative to the surface area of the component of the gas turbine. Moreover, a method is provided in which the angular position of the surface of the at least one vibration means can be adjusted relative to the surface area of the component.
    Type: Grant
    Filed: December 5, 2007
    Date of Patent: January 13, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Erwin Bayer, Max Niegl, Martin Bussmann, Thomas Peschke
  • Method for repairing a guide blade segment for a jet engine
    Patent number: 8914975
    Abstract: A method for repairing a guide blade segment fashioned as a twin guide blade segment within a guide blade composite element, the guide blades being formed from a nose segment and a rear edge segment, the method having identification, within a guide blade segment, of a non-repairable guide blade to be separated from the guide blade composite structure; separation of a non-repairable guide blade from a one repairable guide blade in a first plane of division; division of at least one separated guide blade in a second plane of division between the nose segment and the rear edge segment; reconditioning of the at least one repairable nose segment and/or rear edge segment; joining of a reconditioned and/or new nose segment to a reconditioned and/or new rear edge segment to form at least one guide blade; and joining of at least two guide blades to form a guide blade segment.
    Type: Grant
    Filed: July 13, 2007
    Date of Patent: December 23, 2014
    Assignee: MTU Aero Engines GmbH
    Inventor: Joachim Wulf
  • Circulation structure for a turbo compressor
    Patent number: 8915699
    Abstract: A circulation structure for a turbo compressor, in particular for a compressor of a gas turbine, is disclosed. The circulation structure includes at least one annular chamber that can be traversed in a circumferential direction, is concentric with a shaft of the turbo compressor in the region of the free blade ends of a blade ring, and radially borders a main flow channel. Several chambers that can be traversed in an axial direction are situated upstream of the or each annular chamber, when viewed from the main flow direction of the main flow channel.
    Type: Grant
    Filed: February 19, 2009
    Date of Patent: December 23, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Giovanni Brignole, Carsten Zscherp
  • Method for repairing a rotor system of a turbomachine, annular element for a rotor system of a turbomachine, and rotor system for a turbomachine
    Patent number: 8899919
    Abstract: A method for repairing a rotor system (2) of a turbomachine, having a rotor (4) which has a groove (26) extending in the circumferential direction (58) of the rotor for accommodating an annular section (18; 28). The method has the following steps: chamfering a notch (40) in the groove (26); introducing a recess (44) into the groove (26); and inserting the annular section (18; 28) into the groove (26). At least one engagement element (48; 49) formed on the annular section (18; 28) engages in the recess (44) in order to form a lock against rotation in the circumferential direction (58).
    Type: Grant
    Filed: April 15, 2011
    Date of Patent: December 2, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Christian Heinzelmaier, Michael Raiche, Knut Werner
  • Method for nondestructive testing of workpiece surfaces
    Patent number: 8901515
    Abstract: A method for nondestructive testing of workpiece surfaces by a fluorescent penetration test is disclosed. An embodiment of the method includes a) cleaning the area of the workpiece surface that is to be inspected; b) applying a fluorescent liquid penetrant to the area of the workpiece surface that is to be inspected, where the penetrant penetrates into possible recesses in the workpiece surface; c) removing the excess penetrant from the workpiece surface; d) applying a developer to the area of the workpiece surface that is to be inspected; e) bleaching the fluorescent penetrant by a beam of light in the layer formed by applying the developer to the workpiece surface; and f) visual evaluation of the fluorescent penetrant remaining in the recesses present in the workpiece surface.
    Type: Grant
    Filed: January 18, 2013
    Date of Patent: December 2, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Joachim Bamberg, Wilhelm Satzger
  • Apparatus and method for coating a compressor housing
    Patent number: 8895134
    Abstract: A running-in coating for a compressor housing is disclosed. The running-in coating has at least two layers where a first layer is dimensionally stable and at least one additional layer has run-in capability.
    Type: Grant
    Filed: April 29, 2005
    Date of Patent: November 25, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Wilfried Smarsly, Renate Mendritzki, Horst Mueller-Wittek
  • Rotor and method for manufacturing a rotor for a turbo machine
    Patent number: 8888456
    Abstract: The invention relates to a rotor for a turbo machine, having rotating blades (12), which are joined to a basic rotor body (14), whereby a damping element (24) for damping blade vibrations is provided between blade platforms (10) of at least two adjacent rotating blades (12), damping element (24) being arched radially upward along its axial extent relative to an axis of rotation of the rotor. In addition, the invention relates to a method for manufacturing, repairing, and/or overhauling a rotor for a turbo machine, in which rotating blades (12) are joined to a basic rotor body (14), whereby a damping element (24) for damping blade vibrations is disposed between at least two adjacent rotating blades (12). In this case, damping element (24) is arched radially upward along its axial extent relative to an axis of rotation of the rotor.
    Type: Grant
    Filed: November 14, 2011
    Date of Patent: November 18, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Hans Peter Borufka, Frank Stiehler
  • Material for a gas turbine component, method for producing a gas turbine component and gas turbine component
    Patent number: 8888461
    Abstract: A material for a gas turbine component, to be specific a titanium-aluminum-based alloy material, including at least titanium and aluminum. The material has a) in the range of room temperature, the ?/B2-Ti phase, the ?2-Ti3Al phase and the ?-TiAl phase with a proportion of the ?/B2-Ti phase of at most 5% by volume, and b) in the range of the eutectoid temperature, the ?/B2-Ti phase, the ?2-Ti3Al phase and the ?-TiAl phase, with a proportion of the ?/B2-Ti phase of at least 10% by volume.
    Type: Grant
    Filed: October 18, 2008
    Date of Patent: November 18, 2014
    Assignees: MTU Aero Engines GmbH, Montanuniversitaet Leoben, Boehler Schmiedetechnik GmbH & Co. KG, GFE Metalle Unf Materialien GmbH
    Inventors: Wilfried Smarsly, Helmut Clemens, Volker Guether, Sascha Kremmer, Andreas Otto, Harald Chladil
  • Component for a gas turbine and a method for the production of the component
    Patent number: 8882442
    Abstract: A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base (12) made of a high temperature-resistant nickel alloy and a plurality of turbine blades (14) joined to the rotor base, whereby each turbine blade includes a rotor blade (16) made of a titanium alloy and a blade root. The blade root is configured as an adapter element (18) that is made of a material that can be welded to the titanium alloy as well as to the high temperature-resistant nickel alloy and that is integrally joined to the rotor base (12) and to the rotor blade (16) fusion. A method for the production of the component is also described.
    Type: Grant
    Filed: October 14, 2009
    Date of Patent: November 11, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Wilfried Smarsly, Joachim Bamberg, Joerg Esslinger
  • Modular fuel supply device for a gas turbine including a fuel supply device having an integrated control device
    Patent number: 8881529
    Abstract: A gas turbine, in particular a gas turbine aircraft engine, including a fuel supply device and a control device, wherein at least parts of the control device, in particular of an engine control device, are integrated into the fuel supply device.
    Type: Grant
    Filed: May 9, 2007
    Date of Patent: November 11, 2014
    Assignee: MTU Aero Engines GmbH
    Inventor: Peter Wittmann
  • Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine
    Patent number: 8870542
    Abstract: A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft.
    Type: Grant
    Filed: February 2, 2010
    Date of Patent: October 28, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Manfred Feldmann, Markus Uecker, Benedikt Heidenreich, Dieter Freno
  • Method for producing a component and components of a titanium-aluminum base alloy
    Patent number: 8864918
    Abstract: A method for producing a component of a titanium-aluminum base alloy comprising hot isostatically pressing the alloy to form a blank, subjecting the blank to a hot forming by a rapid solid-blank deformation, followed by a cooling of the component to form a deformation microstructure with high recrystallization energy potential, thereafter subjecting the component to a heat treatment in the range of the eutectoid temperature (Teu) of the alloy, followed by cooling in air, to form a homogeneous, fine globular microstructure composed of phases GAMMA, BETA0, ALPHA2 and having an ordered atomic structure at room temperature. This abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.
    Type: Grant
    Filed: May 3, 2011
    Date of Patent: October 21, 2014
    Assignees: Boehler Schmiedetechnik GmbH & Co. KG, MTU Aero Engines GmbH
    Inventors: Helmut Clemens, Wilfried Wallgram, Martin Schloffer
  • Mask for kinetic cold gas compacting
    Patent number: 8852681
    Abstract: A mask and method for kinetic cold gas compacting is disclosed. The mask includes a body for covering a not-to-be-coated region of a substrate to be coated having a work side exposed to a coating substance. The work side has a hardness such that the work side is not plastic deformable by a striking coating particle.
    Type: Grant
    Filed: November 7, 2009
    Date of Patent: October 7, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Andreas Jakimov, Manuel Hertter, Stefan Schneiderbanger
  • Rotor for a turbo machine
    Patent number: 8851847
    Abstract: The invention relates to a rotor (10) for a turbo machine, in particular for an aircraft turbine, having rotating blades (12), which are joined with a basic rotor body (16) and, radially underneath their blade platforms (18), comprise channels (22) for introducing cooling air (KL) into rotating blades (12), whereby a gas diffusor (24) is provided on a high-pressure (HD) side of rotor (10), this diffusor being designed to at least reduce a hot-gas (HL) flow into channels (22) during the operation of the associated turbo machine and to permit an entry of cooling air (KL) into channels (22), whereby gas diffusor (24) is joined to rotor (10) and comprises a blocking element (28) running annularly in the circumferential direction of rotor (10). A related method for manufacturing, repairing and/or overhauling a rotor (10) for a turbo machine is also provided.
    Type: Grant
    Filed: November 14, 2011
    Date of Patent: October 7, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Hans Peter Borufka, Frank Stiehler
  • Method for manufacturing an integrally bladed rotor
    Patent number: 8826535
    Abstract: The invention relates to a method for manufacturing an integrally bladed rotor, whereby several rotating blades are attached to a basic rotor body by welding in such a way that first, grooves into which the rotating blades are introduced by their blade feet or adapters, and which extend substantially in the axial direction of the basic rotor body, are introduced into the basic rotor body radially outside, prior to attaching the rotating blades, then, the rotating blades are welded to the basic rotor body, wherein the grooves are introduced in the rotor body and the blade feet or adapters are formed on the rotating blades in such a way that a central axis of the grooves is positioned obliquely relative to a central axis of the blade feet or the adapters, so that a pre-twisting is formed on the rotating blades when the rotating blades are introduced into the groove.
    Type: Grant
    Filed: October 10, 2011
    Date of Patent: September 9, 2014
    Assignee: MTU Aero Engines GmbH
    Inventor: Robert Schmidt