Patents Assigned to MTU
  • 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
  • Method for the control and regulation of an internal combustion engine
    Patent number: 8886439
    Abstract: Disclosed is a method for the control and regulation of an internal combustion engine (1), comprising an independent common rail system on the A-side and an independent common rail system on the B-side. During normal operation, the rail pressure (pCR(A), pCR(B)) is controlled in each common rail system via a low pressure-side suction throttle (4A, 4B) as the first pressure-adjusting element in a rail pressure control loop and, at the same time, the rail pressure (pCR(A), pCR(B)) is subjected to a rail pressure disturbance variable via a high pressure-side pressure control valve (11A, 11B) as a second pressure-adjusting element, by means of which a pressure control valve volume flow is redirected via the high pressure-side pressure control valve (11A, 11B) from the rail (6A, 6B) into a fuel tank (2).
    Type: Grant
    Filed: October 20, 2010
    Date of Patent: November 11, 2014
    Assignee: MTU Friedrichshafen GmbH
    Inventor: Armin Dölker
  • High-pressure turbine blade and procedure for repair of high-pressure turbine blades
    Patent number: 8875392
    Abstract: The invention relates to a procedure for repair of high pressure turbine blades of an aircraft engine, with the steps:—separating a damaged section of the high pressure turbine blade; and—generating a section to replace the separated section on or upon the high pressure turbine blade by means of laser beam generation from the powder bed, as well as a high pressure turbine blade.
    Type: Grant
    Filed: October 10, 2007
    Date of Patent: November 4, 2014
    Assignee: MTU Aero Engines AG
    Inventor: Karl-Hermann Richter
  • PROCESS FOR PRODUCING A HIGH-TEMPERATURE PROTECTIVE COATING AND CORRESPONDINGLY PRODUCED COMPONENT
    Publication number: 20140322555
    Abstract: Disclosed is a process for producing a high-temperature protective coating for metallic components, in particular components of turbomachines which are subjected to thermal loading. The process comprises producing a slip from MCrAlY powder, in which M is at least one metal, and from a Cr powder, applying the slip to the component to be coated and subsequently alitizing the component provided with the slip.
    Type: Application
    Filed: April 23, 2014
    Publication date: October 30, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Heinrich WALTER
  • HOUSING SECTION OF A TURBINE ENGINE COMPRESSOR STAGE OR TURBINE ENGINE TURBINE STAGE
    Publication number: 20140321998
    Abstract: A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius.
    Type: Application
    Filed: April 22, 2014
    Publication date: October 30, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Karl Maar, Thomas Hess, Petra Kufner
  • SLIDE RING SEAL
    Publication number: 20140321969
    Abstract: A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall (1) and an inner wall (2) defining the flow channel; and a hollow space (4) being formed between the inner wall and the outer housing wall. The hollow space is separable into at least two regions (5, 6); a movable wire element (slide ring seal) (10, 10?), which is adapted to rest against the contact faces (8, 9), being configured in the hollow space for purposes of the separation.
    Type: Application
    Filed: April 9, 2014
    Publication date: October 30, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Norbert Schinko, Janine Sangl
  • 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
  • Centrifugal pump
    Patent number: 8870522
    Abstract: In a centrifugal pump, in particular a radial or semi-axial pump including a housing with a pump chamber and a dry chamber, a drive shaft rotatably supported in the housing and connected to an impeller for pumping a liquid flow medium disposed in the pump chamber and a shaft seal arranged in an inner radial area for sealing the dry space with respect to the flow medium, a seal carrier is provided with a guide structure by which fluid flow medium is conducted from an outer radial area to an inner radial area for directing flow medium into the seal for lubrication and cooling of the seal.
    Type: Grant
    Filed: March 30, 2011
    Date of Patent: October 28, 2014
    Assignee: MTU Friedrichshafen GmbH
    Inventors: Wolfgang Reischmann, Alexej Vaulin, Joachim Ruck
  • 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
  • Armoring Sealing Fins of TiAl Vanes by Induction Brazing Hard-Material Particles
    Publication number: 20140308117
    Abstract: A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material.
    Type: Application
    Filed: November 6, 2012
    Publication date: October 16, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Bernd Daniels, Karl-Hermann Richter
  • Connection box with a charge air cooling arrangement of an internal combustion engine
    Patent number: 8857416
    Abstract: In a charge air supply arrangement of an internal combustion engine with two stage charging in a combination with first and second charge air coolers, a double connection box is provided with a guide structure including a separation wall defining a lower guide area with a lower connection to the first charge air cooler disposed directly below the double connection box and an upper guide area with an upper connection to the second charge air cooler disposed directly on top of the double connection box. Also, in an internal combustion engine with such a charge air cooling arrangement, the charge air cooler arrangement is arranged on top of the engine.
    Type: Grant
    Filed: April 28, 2012
    Date of Patent: October 14, 2014
    Assignee: MTU Friedrichshafen GmbH
    Inventor: Hermann Baumann
  • Flywheel, internal combustion engine with flywheel and system comprising an internal combustion engine and a machine driven thereby
    Patent number: 8857291
    Abstract: In a flywheel for mounting as a coupling element between an internal combustion engine and a machine to be driven thereby, including a flywheel flange for connecting the flywheel to the machine and a driver flange for connecting the flywheel to the crankshaft of the internal combustion engine, coupling structures are provided between the flywheel flange and the driver flange which coupling structures include insulating connecting areas which electrically insulate the flanges from each other.
    Type: Grant
    Filed: May 7, 2010
    Date of Patent: October 14, 2014
    Assignee: MTU Friedrichshafen GmbH
    Inventors: Christian Schäffer, Martin Kaifler
  • MISCHVORRICHTUNG UND TURBOFANTRIEBWERK MIT EINER DERARTIGEN MISCHVORRICHTUNG
    Publication number: 20140298772
    Abstract: The invention relates to a mixing device and a turbofan engine having such a mixing device 30 for mixing a first gas flow 40 with a second gas flow 50 in a turbofan engine 20, having an actuating device 95 and walls 60, which bound a channel 65 for the first gas flow 40 and a channel 70 lying radially outside for the second gas flow 50, the actuating device 95 comprising a coupling element 110 that is coupled to the walls (60), the actuating device 95 being designed to pivot the walls 60 between a first position and a second position disposed radially outside relative to the first position, the actuating device 95 comprising an adjusting ring 105 that can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element 110.
    Type: Application
    Filed: April 3, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Hermann Klingels, Stephan Klaen, Christian Scherer, Uwe Vogel
  • SECUREMENT SYSTEM AND METHOD FOR SECURING AN ATTACHMENT PORTION OF AT LEAST ONE ROTOR BLADE OR ROTOR BLADE SEGMENT IN A MOUNTING SITE OF A ROTOR BASE
    Publication number: 20140301854
    Abstract: A securement system for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base. The securement system has at least one holder element and a second holder element, each of which has a holding portion and a connecting portion. The connecting portions can be introduced into the mounting site so as to establish a clip connection and can be locked together in the mounting site. The holding portions are configured so as to fasten the attachment portion of the at least one rotor blade or of the rotor blade segment in the mounting site in the locked state of the connecting portions. Further disclosed is a method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base and a rotor having a securement system.
    Type: Application
    Filed: April 4, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Frank STIEHLER, Felix KERN
  • SECURING BLADE ASSORTMENT
    Publication number: 20140301853
    Abstract: A securing plate assortment including multiple different securing plates, the securing plates having different geometric codings. A turbine and method is also disclosed.
    Type: Application
    Filed: April 8, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Martin PERNLEITNER, Rudolf Stanka, Manfred Schill
  • GUIDE VANE ARRANGEMENT
    Publication number: 20140301840
    Abstract: A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward. A pair of axial ribs spaced apart from each other in the peripheral direction and disposed between two adjoining guide vanes in the peripheral direction protrude radially outward from a circumferential surface of the external shroud band and/or axially from a radial flange of the external shroud band.
    Type: Application
    Filed: April 3, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Manuel Hein, Markus Uecker, Rudolf Stanka
  • AIRFOIL HAVING A PROFILED TRAILING EDGE FOR A FLUID FLOW MACHINE, BLADE, AND INTEGRALLY BLADE ROTOR
    Publication number: 20140301860
    Abstract: The present invention relates to an airfoil for a fluid flow machine (100), having a suction side (5), a pressure side (7) and an airfoil trailing edge (200). The airfoil (100), at least in portions thereof, has a profile (9) in the region of the airfoil trailing edge (200), which profile extends over the suction side (5) and the pressure side (7) of the airfoil trailing edge (200). The present invention also relates to a blade and an integrally bladed rotor.
    Type: Application
    Filed: April 8, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Guenter RAMM, Christine Lang
  • BLADE CASCADE FOR TURBO MACHINE
    Publication number: 20140301852
    Abstract: A blade cascade for a turbomachine, in particular a gas turbine, including multiple identical blade groups which are situated next to each other and which each include a first individual blade (10) having a vane (12) having a blade profile and a first side wall (11), and a second individual blade (20), which differs from the first, having a vane (22) having a blade profile and a second side wall (21), the first and second side walls (11, 21) having different contourings.
    Type: Application
    Filed: April 8, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Carsten ZSCHERP
  • Method for regulating the rail pressure in a common rail injection system of an internal combustion engine
    Patent number: 8855889
    Abstract: A method for open-loop and closed-loop control of an internal combustion engine (1) in which the rail pressure (pCR) is controlled via a low pressure-side suction throttle (4), as the first pressure-adjusting element in a rail pressure control loop. A rail pressure disturbance variable (VDRV) is generated to influence the rail pressure (pCR) via a high-pressure side pressure control valve (12), as the second pressure-adjusting element, by which fuel is redirected from the rail (6) into the fuel tank (2). The position of the high-pressure side pressure control valve (12) is determined by a PWM signal (PWMDV), which, when normal mode is set, is calculated as a function of the resulting target volume flow and, when protective mode is set, is temporarily set to a maximum value.
    Type: Grant
    Filed: June 17, 2010
    Date of Patent: October 7, 2014
    Assignee: MTU Friedrichshafen GmbH
    Inventor: Armin Dölker
  • 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