Patents Assigned to MTU
  • Patent number: 10385434
    Abstract: An apparatus and a process for producing forged components composed of TiAl alloys, wherein a melt of a TiAl alloy is provided and is cast by horizontal centrifugal casting so as to produce at least one semifinished TiAl cast part and the semifinished TiAl cast part is converted by forging into a forged TiAl part.
    Type: Grant
    Filed: June 23, 2016
    Date of Patent: August 20, 2019
    Assignee: MTU AERO ENGINES AG
    Inventors: Martin Schloffer, Wilfried Smarsly, Marc Haltrich
  • Patent number: 10385783
    Abstract: The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells (1-3) connected to one another in the circumferential direction (U), wherein shells adjacent in the axial direction have cross sections opened counter to a throughflow direction (A) and/or a thread axis inclined counter to the throughflow direction.
    Type: Grant
    Filed: January 22, 2013
    Date of Patent: August 20, 2019
    Assignee: MTU AERO ENGINES AG
    Inventors: André Werner, Steffen Schlothauer, Franz Prieschl, Thomas Hess
  • Publication number: 20190249569
    Abstract: The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, comprising an additively built-up housing section and a cover, which, in each case referred to an axis of rotation of the shaft, connects axially to the housing section and has a radially extending collar, which collar axially bounds an oil space of the bearing chamber housing, wherein the cover is assembled with the housing section and is connected therewith via a weld.
    Type: Application
    Filed: February 7, 2019
    Publication date: August 15, 2019
    Applicant: MTU Aero Engines AG
    Inventors: Frank Stiehler, Georg Kempinger, Juergen Kraus, Steffen Schlothauer, Christian Liebl, Thomas Koebke, Alois Eichinger
  • Publication number: 20190249562
    Abstract: Disclosed is a lever connection for a guide vane adjustment for connecting a guide vane of a turbomachine to an adjusting ring of an actuator, which is arranged in such a way that an adjusting lever of the lever connection is pushed radially from a first mounting direction, in relation to a machine longitudinal axis of the turbomachine, onto a vane shaft of the guide vane, and is locked with the vane shaft in a form-fitting and, in particular, rotationally rigid manner by means of a movement in a second mounting direction; a mounting method; and a turbomachine.
    Type: Application
    Filed: February 10, 2019
    Publication date: August 15, 2019
    Applicant: MTU Aero Engines AG
    Inventor: Werner Humhauser
  • Patent number: 10371054
    Abstract: A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: August 6, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Stefan Sasse, Erwin Bayer
  • Patent number: 10370989
    Abstract: The invention relates to a guide vane segment for a gas turbine comprising at least one radially outer shroud and one radially inner shroud, which extend along a respective arc and together form an annular segment, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacent to one another in the peripheral direction and are joined to the inner shroud and to the outer shroud in a material-bonded manner and, in particular, are joined in a one-piece manner, wherein, in an axial lengthwise direction, the outer shroud comprises an axially front end wall element and an axially rear end wall element in such a way that the outer shroud and the two end walls form a tub-like profile in lengthwise section.
    Type: Grant
    Filed: December 2, 2016
    Date of Patent: August 6, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Manfred Feldmann, Rudolf Stanka, Oliver Thiele, Bernd Kislinger, Manuel Hein
  • Publication number: 20190234225
    Abstract: The present invention relates to a module for a turbomachine, having a guide vane arrangement and a seal carrier, which is arranged, with reference to a longitudinal axis of the module, radially inside an inner platform of the guide vane arrangement, wherein, in each case with reference to the longitudinal axis of the module, when considered in an axial section, the seal carrier has a radially extending seal carrier wall and a sealing web extending axially away from it, which forms a labyrinth seal together with the inner platform of the guide vane arrangement, wherein the seal carrier wall and the sealing web are made up in one piece with each other, i.e., they are built up additively together.
    Type: Application
    Filed: January 28, 2019
    Publication date: August 1, 2019
    Applicant: MTU Aero Engines AG
    Inventor: Christoph Lauer
  • Patent number: 10363606
    Abstract: A device for the generative production of a component, particularly a component of a gas turbine engine, includes a working chamber, a hardening means, in particular a laser, for the layerwise local hardening of an initial material disposed in the working chamber, in order to produce the component layerwise in a direction of layer construction; and a movable induction heating arrangement with a first inductor and a second inductor for induction tempering in pre-determinable regions of the working chamber, wherein the first inductor engages in the second inductor at least in one operating position and/or the first and/or second inductor is disposed on a distribution means, in particular a slider, for the layerwise disposal of initial material in the working chamber.
    Type: Grant
    Filed: February 23, 2015
    Date of Patent: July 30, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Georg Schlick, Andreas Jakimov, Herbert Hanrieder
  • Patent number: 10364827
    Abstract: An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed.
    Type: Grant
    Filed: March 30, 2015
    Date of Patent: July 30, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Hermann Klingels
  • Patent number: 10364686
    Abstract: A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface.
    Type: Grant
    Filed: May 27, 2014
    Date of Patent: July 30, 2019
    Assignee: MTU AERO ENGINES AG
    Inventors: André Werner, Wilfried Smarsly
  • Publication number: 20190226352
    Abstract: The present invention relates to a rotor blade shroud for a turbomachine, comprising a sealing tip and a support structure that abuts the sealing tip. The support structure has at least one intermediate region in which a structural segment is arranged, wherein the radially outwardly arranged surface of the support structure and of the structural segment forms an essentially planar surface. The present invention further relates to a rotor blade for a turbomachine, comprising a rotor blade shroud as well as two methods of manufacturing a rotor blade shroud and a method of manufacturing a rotor blade.
    Type: Application
    Filed: January 22, 2019
    Publication date: July 25, 2019
    Applicant: MTU Aero Engines AG
    Inventor: Jochen Gier
  • Patent number: 10352178
    Abstract: A locking element for a row of blades of a turbomachine includes a number of blades that are inserted by their roots in an anchoring groove on the rotor side and are thereby held in the radial direction in form-fitting manner in the anchoring groove. The locking element has a basic body that has a front bearing surface and a back bearing surface for form-fitting with opposite-lying groove surfaces, a front lock projection and a back lock projection for engaging in opposite-lying recesses of the anchoring groove, and a threaded region for interacting with a tightening element. Access to the threaded region for the tightening element is blocked on one side.
    Type: Grant
    Filed: February 15, 2016
    Date of Patent: July 16, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Hermann Klingels
  • Patent number: 10352261
    Abstract: A method for operating an internal combustion engine, in particular a gas engine, having two cylinder banks, each of which includes multiple cylinders, wherein each cylinder bank is independently supplied with charging pressure, and having a device for actively deactivating at least one cylinder of each cylinder bank. When the operating state is switched from a state with at least one deactivated cylinder to an operating state with at least one other activated cylinder, the charging pressure is reduced prior to the activation of the other cylinder.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: July 16, 2019
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Thorsten Konrad, Wolfgang Fimml, Alexander Bernhard
  • Publication number: 20190211708
    Abstract: The present invention relates to a housing arrangement for a turbomachine, comprising a support element, which is configured to bear a shaft, and a housing, which is centered at the support element. The housing is composed of an inner housing and an outer housing fastened at the support element, the housings being connected to each other by at least one connecting strut. A press fit is provided between the support element and the inner housing, in order to center the inner housing at the support element.
    Type: Application
    Filed: December 17, 2018
    Publication date: July 11, 2019
    Applicant: MTU Aero Engines AG
    Inventors: Georg Kempinger, Johann Berger, René Grahnert, Johannes Dieker, Tanya Mulorz, Laura Martinez-Lozano
  • Publication number: 20190211742
    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: Application
    Filed: March 18, 2019
    Publication date: July 11, 2019
    Applicant: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Andreas HOHNER, Konstantin RUNDEL
  • Patent number: 10343308
    Abstract: Equipment for the generative manufacture and/or repair of components, in particular of gas turbines, includes a solidifying means for the layer-by-layer, local, particularly optical, thermal, and/or chemical solidification of particularly powdered, granular, and/or fluid material, and an electrodeposition means for the electrostatic deposition of particles and/or gas from a region between a layer of material, which is to be solidified or is solidified, and the solidifying means, as well as a method for the generative manufacture and/or repair of components, in particular of gas turbines, by means of such equipment.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: July 9, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Thomas Hess, Georg Schlick, Alexander Ladewig
  • Patent number: 10337519
    Abstract: Disclosed is a method for operating a compressor of a turbomachine, in which, when viewed in the direction of a main flow, a slowly dropping degree of reaction being raised in one compressor area more quickly than previously dropped and the raised degree of reaction then being reduced again in a subsequent compressor area more slowly that it was previously raised, a compressor of a turbomachine including at least one degree of reaction rising more quickly in one compressor area in comparison to adjacent compressor areas with respectively a dropping degree of reaction, whereby a sawtooth-shaped curve of the degree of reaction results, and a turbomachine including a compressor of this type.
    Type: Grant
    Filed: November 23, 2016
    Date of Patent: July 2, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Sergio Elorza Gomez, Tim Schneider
  • Patent number: 10329952
    Abstract: A bearing assembly (2) is provided, in particular for a turbomachine, including: an inner bearing race (3); an outer bearing race (4) having at least one cooling channel (15) formed within it or in its outer surface; rolling elements (7) made of ceramic and disposed between the inner bearing race (3) and the outer bearing race (4); and a surrounding bearing ring (9) connected to the outer bearing race (4) and configured to form a squeeze film (10) of oil between its outer surface and an opposite inner surface of a housing (1) in which the bearing assembly can be mounted.
    Type: Grant
    Filed: July 27, 2017
    Date of Patent: June 25, 2019
    Assignees: MTU Aero Engines AG, Schaeffler Technologies AG & Co. KG
    Inventors: Michael Flouros, Peter Gloeckner, Patrick Mirring, Matthias Martin
  • Publication number: 20190186417
    Abstract: The present invention relates to a turbine module for a turbomachine, comprising a first flow bypass structure and a second flow bypass structure, said flow bypass structures being arranged in a hot gas duct, which is bounded by the turbine module and is designed to convey a hot gas and, namely, being arranged in succession in relation to a longitudinal axis of the turbine module in a direction of rotation, wherein, in relation to the bypass flow in the hot gas duct, the flow bypass structures each have a leading edge, and, downstream thereto, a trailing edge, and the second flow bypass structure is provided as a deflecting blade, wherein the second flow bypass structure has a smaller profile thickness than the first flow bypass structure, and wherein the hot gas duct is enclosed by a radial width.
    Type: Application
    Filed: December 13, 2018
    Publication date: June 20, 2019
    Applicant: MTU Aero Engines AG
    Inventors: Guenter Ramm, Martin Hoeger, Irene Raab, Yavuz Guendogdu
  • Patent number: 10323527
    Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.
    Type: Grant
    Filed: July 3, 2014
    Date of Patent: June 18, 2019
    Assignee: MTU Aero Engines GmbH
    Inventors: Hans Stricker, Stefan Rauscher, Willem Bokhorst