Patents Assigned to MTU
  • Patent number: 8663814
    Abstract: An anti-wear coating, in particular an anti-erosion coating, which is applied to a surface of a component that is stressed under fluid technology and is to be protected, in particular a gas turbine part, is disclosed. The anti-wear coating includes one or more multilayer systems applied in a repeating order to the surface to be coated, and the/each multilayer system includes at least one relatively soft metallic layer and at least one relatively hard ceramic layer. All the layers of the/each multilayer system are based on chromium, and a diffusion barrier layer is applied between the surface to be protected and the multilayer system(s).
    Type: Grant
    Filed: May 17, 2008
    Date of Patent: March 4, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Wolfgang Eichmann, Falko Heutling, Thomas Uihlein
  • Patent number: 8653411
    Abstract: A pulsed machining method for the optimized machining of a contour which is characterized in that the instantaneous frequency ratio of ? of the pulse frequency of tool fL and of the rotational frequency of tool fCNC is optimized to achieve a highest possible degree of coverage of the individual machining pulses in the context of a shortest possible machining duration and without a direct concatenation of the machining pulses. It is especially preferred that this be achieved in that frequency ratio ? is an irrational number, thus cannot be expressed by the ratio of two whole numbers. By applying the method according to the present invention, a considerable time savings is achieved since there is no longer a need for time-consuming preliminary trials to ascertain an at least sufficient frequency ratio ?.
    Type: Grant
    Filed: February 24, 2009
    Date of Patent: February 18, 2014
    Assignee: MTU Aero Engines GmbH
    Inventor: Mark Geisel
  • Patent number: 8650920
    Abstract: A method and device for surface peening, particularly ultrasonic shot peening, of a component in the region of a passage opening is disclosed. A vibration device impinging the blasting material is disposed on one side and a counter-element is disposed on an opposite side relative to a component region having the passage opening. The counter-element is disposed at a distance relative to the corresponding side of the component region.
    Type: Grant
    Filed: June 6, 2008
    Date of Patent: February 18, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Erwin Bayer, Eggert Reese, Juergen Steinwandel
  • Publication number: 20140044546
    Abstract: A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2).
    Type: Application
    Filed: July 25, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Johann GEPPERT, Peter Eibelshaeuser
  • Publication number: 20140044537
    Abstract: A gas turbine stage, in particular a low-pressure compressor stage, for a gas turbine, in particular an aircraft engine gas turbine having a guide vane assembly having at least one guide vane (1) having a radially inner guide vane root (1.1), on which a sealing ring element (2) is supported by a spoke-type centering that has an inner wall (1.2) and a circumferential groove (2.1, 2.2) receiving the same, the inner wall having at least one face (1.4) facing a groove inner surface of the circumferential groove and a flank (1.5) adjacent thereto and angled therefrom; a rounded portion, in particular a radius (R) being formed between the face and the flank.
    Type: Application
    Filed: August 5, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Hans-Peter Hackenberg
  • Publication number: 20140044551
    Abstract: A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one pressure-side elevation and one suction-side depression, whose highest section and lowest section are located over an area 30% to 60% of an extension of the blades in the axial direction, and the axial positions of the outermost sections differ from each other at the maximum by 10% in the axial direction.
    Type: Application
    Filed: August 1, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Inga Mahle, Markus Brettschneider
  • Publication number: 20140044550
    Abstract: A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Felix KERN, Frank Stiehler, Stephan Klaen
  • Publication number: 20140044532
    Abstract: Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising: forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Applicant: MTU AERO ENGINES AG
    Inventor: Karl-Hermann RICHTER
  • Publication number: 20140044526
    Abstract: Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type.
    Type: Application
    Filed: August 2, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Werner Humhauser
  • Publication number: 20140044938
    Abstract: Disclosed is process for producing a protective layer for protecting a component against high temperatures and aggressive media. The process comprises forming a surface layer comprising aluminum and chromium on a surface of the component to be provided with the protective layer by chromizing and alitizing. The chromizing and/or the alitizing in different regions of the component surface to be protected is carried out simultaneously but differently to result in a protective layer that has different regions.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Applicant: MTU AERO ENGINES AG
    Inventors: Horst PILLHOEFER, Erwin BAYER, Thomas DAUTL, Stefan MUELLER
  • Publication number: 20140044986
    Abstract: Disclosed is a coating for protecting a component against high temperatures and aggressive media, which coating has at least one subregion whose main constituent is chromium. The layer additionally comprises aluminum, the chromium content at least in the subregion in which chromium is the main constituent being greater than 30% by weight and the aluminum content being greater than or equal to 5% by weight. The invention further provides a process for producing such a coating, comprising chromizing the surface to be coated and subsequently alitizing the chromium-rich layer produced during chromizing.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Applicant: MTU AERO ENGINES AG
    Inventors: Horst PILLHOEFER, Stefan Mueller, Erwin Bayer, Thomas Dautl
  • Publication number: 20140044549
    Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. In the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.
    Type: Application
    Filed: August 9, 2013
    Publication date: February 13, 2014
    Applicant: MTU AERO ENGINES AG
    Inventors: Erich Steinhardt, Wilfried Smarsly, André Werner
  • Patent number: 8649158
    Abstract: The present invention relates to a capacitor arrangement having a capacitor and a first terminal plate and a second terminal plate. The capacitor has a first contact face and a second contact face arranged opposite one another. The terminal plates are each connected to one of the contact faces and have protrusions on one end suitable for engaging in recesses in a power rail.
    Type: Grant
    Filed: October 8, 2009
    Date of Patent: February 11, 2014
    Assignee: MTU Aero Engines AG
    Inventors: Hubert Herrmann, Werner Riebesel, Jürgen Kneissl
  • Publication number: 20140032189
    Abstract: In a method for a model-based determination of a temperature distribution of an exhaust gas post-treatment unit, a differentiation is made between steady operating states and non-steady operating states by taking into account the axial and the radial temperature distribution, and, on the basis of virtual segmentation of the post-treatment unit, in particular the radial heat transfer to the surroundings is taken into account in the model-based determination for steady operating states, and for non-steady operating states the heat transfer from the exhaust gas which flows axially through the post-treatment unit to the segments is taken into account by a heat transfer coefficient k.
    Type: Application
    Filed: February 7, 2012
    Publication date: January 30, 2014
    Applicant: MTU Friedrichshafen GmbH
    Inventors: Marc Hehle, Ralf Müller, Jens Niemeyer, Jörg Remele, Guido Schäffner, Holger Sinzenich, Tim Späder
  • Publication number: 20140030810
    Abstract: A method and an arrangement for dynamic breakthrough detection is proposed. The arrangement comprises at least a transfer element, at least a memory unit in which sensor characteristic curves, at least a controller and an evaluation logic are stored.
    Type: Application
    Filed: February 7, 2012
    Publication date: January 30, 2014
    Applicant: MTU Friedrichshafen GmbH
    Inventor: Jens Niemeyer
  • Publication number: 20140026560
    Abstract: A relief valve for turbines of exhaust turbochargers. Hot exhaust gas flows against this type of relief valves and the relief valves heat up significantly. Sensitive components such as the springs or the membrane can be damaged as a result. The relief valves are normally designed so that the membrane and a radiation panel are adjacent to a first chamber. Air is continuously guided through the first chamber in order to specifically cool the membrane and protect the membrane from excessive heating.
    Type: Application
    Filed: March 8, 2012
    Publication date: January 30, 2014
    Applicant: MTU Friedrichshafen Gmbh
    Inventor: Michael Dobrowolski
  • Patent number: 8635772
    Abstract: A method for the milling machining of components is disclosed. The method produces recesses with one or more lateral walls, in particular for the production of integrally bladed rotors for gas turbines, the recesses forming flow channels and the lateral walls forming blade surfaces of an integrally bladed rotor. The component to be machined by milling is clamped in a locating device for the milling machining. To adjust the vibrational properties of the component to be machined by milling, areas of the component are embedded in and/or filled with a machinable plastic.
    Type: Grant
    Filed: January 12, 2007
    Date of Patent: January 28, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Stefan Heinrich, Arndt Glaesser, Goetz Lebkuechner
  • Patent number: 8628291
    Abstract: A gas turbine compressor is disclosed. The compressor includes a compressor housing, guide vanes, rotor blades, and valve-controlled blow-in openings for stabilizing the compressor flow by air that is blown in. The air flow is detected by pressure sensors and the valves are controlled as a function thereof.
    Type: Grant
    Filed: April 2, 2009
    Date of Patent: January 14, 2014
    Assignee: MTU Aero Engines GmbH
    Inventor: Sven-J. Hiller
  • Patent number: 8622704
    Abstract: The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into gas turbine blade (10). The invention further relates to a shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.
    Type: Grant
    Filed: November 12, 2010
    Date of Patent: January 7, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Frank Stiehler, Hans Peter Borufka, Patrick Prokopczuk
  • Patent number: 8623165
    Abstract: A device for fixing a component (4) in position on a component carrier (6) using a radiation-curing adhesive agent (8), in which case the radiation (30, 32) for curing the adhesive agent (8) located between the component carrier (6) and the component (4) is laterally introducible; as well as a method for fixing a component (4) in position in a component carrier (6) using an adhesive bond.
    Type: Grant
    Filed: May 8, 2010
    Date of Patent: January 7, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Martin Fessler-Knobel, Roland Huttner