Patents Assigned to MTU
  • Publication number: 20200230744
    Abstract: The present invention relates to a method for producing a component of a turbomachine from a metal alloy as well as a correspondingly produced component, wherein the method includes defining at least one first component region that will have a first property profile, and at least one second component region that will have a second property profile which is different from the first property profile; providing at least one powder of the metal alloy or several different powders of constituents of the metal alloy; additive manufacture of the component from the at least one powder, wherein the powder is melted for cohesive joining of the powder particles to each other and to a substrate or to an already produced part of the component.
    Type: Application
    Filed: January 16, 2020
    Publication date: July 23, 2020
    Applicant: MTU Aero Engines AG
    Inventor: Markus Fried
  • Patent number: 10711628
    Abstract: A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.
    Type: Grant
    Filed: October 24, 2017
    Date of Patent: July 14, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Lothar Albers, Thomas Binsteiner, Johann Geppert, Stefan Herbst, Manuel Hertter, Alexander Scharf, Robert Winsy, Stephen Royston Williams
  • Patent number: 10711798
    Abstract: A variable vane cascade for a turbomachine, in particular for a compressor stage or turbine stage of a gas turbine, having at least one first vane, in particular guide vane that has a first distance from a circumferentially adjacent vane, at least one second vane, in particular guide vane that has at least one second distance from at least one circumferentially adjacent vane that is smaller than the first distance, and an actuating device, in particular for jointly and/or reversibly adjusting the first and second vane from a first position where at least one airfoil cross section of the first vane and an airfoil cross section of the second vane each have a first stagger angle, into a second position where these airfoil cross sections have second stagger angles, the second stagger angle of the first vane differing from the second stagger angle of the second vane, in particular being larger than the second stagger angle of the second vane.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: July 14, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Alexander Halcoussis
  • Patent number: 10711626
    Abstract: The invention is directed to a guide vane ring for a turbomachine, in which a vane bearing is produced in the inner ring via platform plates of the vanes and reliability against disintegration is produced via journals that extend radially inward from the platform plates, as well as a turbomachine.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: July 14, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Hermann Klingels
  • Patent number: 10704393
    Abstract: Disclosed is an airfoil array segment (110, 120, 130, 140, 150) of an airfoil array for a turbomachine, the airfoil array segment including a platform (10) having a platform surface, as well as at least two airfoils (20, 30). The platform surface has a depression (111, 121, 131, 141, 151) which extends up to the first airfoil and contacts the pressure side (21) of the first airfoil downstream of 80% of the axial chord (g) downstream of the leading edges (23, 33) and which contacts the pressure side (21) of the first airfoil downstream up to no more than 80% of the axial chord (g) downstream of the leading edges (23, 33). At least one lowest point (112, 122) of the depression is located at least 90% of the axial chord (g) downstream of the leading edges (23, 33). Also disclosed are an airfoil array, an airfoil passage, a platform, a turbomachine, and an aircraft engine.
    Type: Grant
    Filed: May 9, 2018
    Date of Patent: July 7, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Fadi Maatouk, Markus Brettschneider, Inga Mahle
  • Publication number: 20200200030
    Abstract: Disclosed is a static seal arrangement for sealing a gap between a first static component and a second static component of a turbomachine such as an aircraft engine or a static gas turbine, having a brush seal held distant from a hot gas, this brush seal being arranged standing or vertical with its clamping section that can be surrounded by cooling air in a radially outer clamping space relative to the gap, and forming a radial sealing site with the first component and an axial sealing site with the second component; also disclosed is a turbomachine.
    Type: Application
    Filed: December 5, 2019
    Publication date: June 25, 2020
    Applicant: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Simon Schmalfuss
  • Publication number: 20200198010
    Abstract: The invention relates to a method for additive production of a component layer of a component including the steps of: generating at least one layer from a powdery component material in the region of a structuring and joining zone; subdividing model data of the layer into virtual sub-regions by a control device; selecting at least one of the virtual sub-regions by the control device; localized heating of at least one heating region in a real sub-region of the layer corresponding with the selected virtual sub-region by a heating device; verifying whether a temperature of the layer has, in a predetermined inspection region, a predetermined minimum temperature; and localized solidifying of the layer in a predetermined solidifying region by selective irradiation by at least one energy beam of an energy source, if the layer has the predetermined minimum temperature in the inspection region.
    Type: Application
    Filed: July 27, 2018
    Publication date: June 25, 2020
    Applicants: EOS GmbH Electro Optical Systems, MTU Aero Engines AG
    Inventors: Sebastian EDELHÄUSER, Martin LEUTERER, Michael GÖTH, Bernd BIECHELE, Markus FROHNMAIER, Gerd CANTZLER, Johannes CASPER
  • Publication number: 20200200015
    Abstract: A rotor blade airfoil (25) for a turbomachine (1) that is adapted for rotation about a longitudinal axis (2) of the turbomachine (1) is provided. The rotor blade airfoil (25) is built from an airfoil material reinforced with a fibrous material (30). At least a portion of the fibers of the fibrous material (30), in particular at least 20%, preferably at least 30% of the fibers, are oriented in a first fiber direction (31), and the first fiber direction (31) is tilted with respect to the stacking axis of the rotor blade airfoil (25).
    Type: Application
    Filed: December 16, 2019
    Publication date: June 25, 2020
    Applicant: MTU Aero Engines AG
    Inventors: Benedikt ALBERT, Siegfried SIKORSKI
  • Patent number: 10690076
    Abstract: A method for compensating valve drift in an internal combustion engine having a variable valve train; in the method, an actual value of the current operating state of the internal combustion engine is determined in an air expenditure map and compared to a desired value of the air expenditure map, whereupon the air expenditure map is corrected.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: June 23, 2020
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Jan Boyde, Wolfgang Fimml, Erika Schäfer
  • Patent number: 10689983
    Abstract: An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: June 23, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Gerhard-Heinz Roesele, Martin Pernleitner, Manfred Schill, Manfred Feldmann, Adrian Ehrenberg
  • Publication number: 20200190986
    Abstract: The present invention relates to an impulse body module group with at least two impulse body modules, which, in particular, are identical in construction, for a gas turbine blade, wherein each of the impulse body modules comprises a housing, which, in particular, is of one piece and which has a first cavity, which is closed, in particular in an airtight manner, by a first cover, which is joined to the housing, in particular in a material-bonded manner, and in which a single, in particular spherical or cylindrical, first impulse body is accommodated with play of movement in at least one first direction of impact, wherein the housing has no additional cavity or a single additional cavity, in which a single, in particular spherical or cylindrical, additional impulse body is accommodated with play of movement in at least one direction of impact.
    Type: Application
    Filed: December 12, 2019
    Publication date: June 18, 2020
    Applicant: MTU Aero Engines AG
    Inventors: Karl-Hermann Richter, Herbert Hanrieder, Steffen Gerloff
  • Patent number: 10677080
    Abstract: A seal system for a moving blade system of a gas turbine includes a seal carrier including a ring section extending in the axial direction and the circumferential direction, on which a radially inner seal element is situated. A first flange section and a second flange section extend outwardly from the ring section in the circumferential direction and the radial direction and are situated at a distance from each other in the axial direction. An inner shroud section of at least one guide blade or of at least one guide blade segment includes a sealing section extending inwardly in the radial direction and in the circumferential direction, the sealing section being accommodated between the first flange section and the second flange section of the seal carrier and being connected thereto. A disk-like first seal is situated upstream from the first flange section with respect to the main flow direction of a working medium and partially abuts the first flange section radially inwardly.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: June 9, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Hermann Klingels
  • Patent number: 10677076
    Abstract: A guide vane ring for a turbomachine minimizes a leakage flow that passes through a recess into which a guide vane disk is inserted. It has a guide vane row having a plurality of guide vanes, each having a vane airfoil and a vane disk, as well as an inner ring having an inner ring surface facing the plurality of guide vanes. Viewed in the direction of a designated primary flow streaming through the turbomachine, the vane disks have a front and a rear surface region. In a nominal and/or a maximum open position of the guide vanes, the front and/or the rear surface region of at least one of the vane disks has an offset from the inner ring surface that is radially disposed (relative to a central axis of the inner ring).
    Type: Grant
    Filed: April 26, 2017
    Date of Patent: June 9, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Hannes Wolf, Alexander Halcoussis
  • Patent number: 10669962
    Abstract: A method for predictive open-loop and/or closed-loop control of an internal combustion engine with control variables pursuant to a model of the engine with characterizing variables and a control circuit for the control variables. The control variables are adjusted in an open-loop or closed-loop manner by measuring actual values and specifying target values of the characterizing variables and, optionally, depending on the boundary and/or environmental and/or ageing conditions. The characterizing variables are controlled pursuant to a model of the engine with the characterizing variables and a control circuit with the control variables. The controlling is part of a model-based predictive control, wherein the characterizing variables of the engine model are calculated and the control variables of the engine are adjusted in a predictively controlled manner.
    Type: Grant
    Filed: October 10, 2016
    Date of Patent: June 2, 2020
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Michael Buchholz, Knut Graichen, Karsten Harder, Jens Niemeyer, Jörg Remele
  • Patent number: 10662867
    Abstract: In an internal combustion engine with exhaust gas turbochargers which operate in parallel and of which at least one can be switched on and off by a charge air duct blocking arrangement including a charge air duct blocking element, the charge air duct blocking arrangement is adapted to provide for a certain movement characteristic of the charge air duct blocking element resulting in a slower movement of the charge air duct blocking element resulting in a longer duration for the air duct blocking element to reach its open position and a faster movement during closing resulting in a rapid closing of the charge air duct blocking element.
    Type: Grant
    Filed: March 18, 2019
    Date of Patent: May 26, 2020
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Andreas Hohner, Konstantin Rundel
  • Publication number: 20200158013
    Abstract: A method for operating an internal combustion engine having an engine with a first number of cylinders and a second number of cylinders and a supercharger arrangement, wherein a charge air flow supplied to the engine is compressed by means of at least one compressor and at least one turbine is acted on by an exhaust gas flow discharged from the engine. In a main operating mode, the engine operates the first number of cylinders in two-stroke operation and the second number of cylinders in four-stroke operation. A scavenging gradient of the engine is greater for the cylinders operated in the two-stroke operation than for the cylinders operated in the four-stroke operation.
    Type: Application
    Filed: November 18, 2019
    Publication date: May 21, 2020
    Applicant: MTU Friedrichshafen GmbH
    Inventors: Günther Schmidt, Ralf Speetzen
  • Patent number: 10655483
    Abstract: A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: May 19, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Martin Pernleitner, Manfred Dopfer, Marcus Woehler, Oliver Thiele, Bernd Kislinger, Norman Cleesattel, Christoph Lauer, Manfred Schill, Manuel Hein
  • Patent number: 10655490
    Abstract: A seal arrangement comprising a first and second components made of a ceramic fiber composite material and comprising first and second bounding sections with first and second overlapping sections and first and second securing sections which are connected to and projects from the first and second bounding sections. The first and second overlapping sections are arranged at least partially overlapping such that the first and second bounding sections form an essentially continuous bounding surface. A separation between the first and second securing sections is at least partially sealed by a seal element which comprises at least one first sheet-metal element arranged along the first securing section and at least partially bridging the separation between the first and second securing sections.
    Type: Grant
    Filed: February 12, 2018
    Date of Patent: May 19, 2020
    Assignee: MTU AERO ENGINES AG
    Inventor: Alexander Boeck
  • Patent number: 10654137
    Abstract: The present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components (1, 10) of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps: preparing the area to be repaired, in order to provide a smooth and clean surface (4), applying an Ni-based braze (7) with a proportion of hard material particles (8) to the surface (4) to form a repair layer (15), wherein the hard material particles comprise hard alloys based on cobalt or nickel, heat treating the component to braze the repair layer onto the component under vacuum conditions.
    Type: Grant
    Filed: October 6, 2016
    Date of Patent: May 19, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Bernd Daniels, Michael Hillen, André Werner
  • Patent number: 10646962
    Abstract: The invention relates to a method for producing a low-pressure turbine blade from a TiAl material by means of a selective laser melting process, wherein during production in the selective laser melting process the already partially manufactured low-pressure turbine blade is preheated by inductive heating, and wherein the selective laser melting process is carried out under protective gas, the protective gas atmosphere containing contaminants of oxygen, nitrogen, and water vapor in each case of less than or equal to 10 ppm.
    Type: Grant
    Filed: March 28, 2013
    Date of Patent: May 12, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Karl-Hermann Richter, Herbert Hanrieder