Patents Assigned to MTU
  • Turbomachine stage and method for detecting a sealing gap of such a turbomachine stage
    Patent number: 9784120
    Abstract: A turbomachine stage, in particular a turbine stage or compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, in particular conical, housing in which a rotor blade arrangement having a plurality of rotor blades is disposed which have an outer shroud having at least one radial sealing flange. The sealing flange has a recess arrangement having at least one radial recess in which a radial projection is disposed, in particular centrally. A sensor arrangement having at least one capacitive sensor for detecting a radial distance from a circumferential surface of the sealing flange is disposed on the housing.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: October 10, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Michael Zielinski, Andreas Zeisberger, Rene Schneider
  • Sealing arrangement for a turbomachine, a guide vane arrangement, and a turbomachine with such a sealing arrangement
    Patent number: 9784131
    Abstract: The invention relates to a sealing arrangement 15, a guide vane arrangement, and a turbomachine 11 with such a sealing arrangement 15, wherein the sealing arrangement 15 is designed for a guide vane ring 60 of a turbomachine 11, wherein the sealing arrangement 15 comprises a thin-walled annular structure 80 that is substantially closed on all sides, and wherein the annular structure 80 delimits an annular interior space 105, wherein a hollow cell structure 109, which is designed so as to mechanically support the annular structure 80, is provided in the annular interior space 105.
    Type: Grant
    Filed: June 23, 2014
    Date of Patent: October 10, 2017
    Assignee: MTU AERO ENGINES AG
    Inventors: Manfred Feldmann, Karl-Heinz Dusel
  • Method for model-based determination of a temperature distribution of an exhaust gas post-treatment unit
    Patent number: 9779218
    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: Grant
    Filed: February 7, 2012
    Date of Patent: October 3, 2017
    Assignee: MTU Friedrichshafen GmbH
    Inventors: Marc Hehle, Ralf Müller, Jens Niemeyer, Jörg Remele, Guido Schäffner, Holger Sinzenich, Tim Späder
  • Brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another
    Patent number: 9777588
    Abstract: A brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another includes a gas seal housing that receives at least one brush head of a brush seal and a support element by means of which a brush packet projecting from the brush head of the brush seal may be supported against flexing. The support element and the brush seal housing are embodied as separate components. The invention furthermore relates to a method for producing such a brush seal system and to a thermal gas turbine having such a brush seal system.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: October 3, 2017
    Assignee: MTU AERO ENGINES AG
    Inventors: Stephan Klan, Frank Stiehler, Julian Weber, Markus Schlemmer, Stephan Prostler
  • Housing section of a turbine engine compressor stage or turbine engine turbine stage
    Patent number: 9771830
    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: Grant
    Filed: April 22, 2014
    Date of Patent: September 26, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Karl Maar, Thomas Hess, Petra Kufner
  • Mixing device and turbofan engine having such mixing device
    Patent number: 9771896
    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: Grant
    Filed: April 3, 2014
    Date of Patent: September 26, 2017
    Assignee: MTU AERO ENGINES AG
    Inventors: Hermann Klingels, Stephan Klaen, Christian Scherer, Uwe Vogel
  • Damping device for being situated between a housing wall and a casing ring of a housing of a thermal gas turbine
    Patent number: 9771827
    Abstract: A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.
    Type: Grant
    Filed: July 22, 2014
    Date of Patent: September 26, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Rudolf Stanka, Thomas Hess, Karl Maar, Karl-Heinz Dusel
  • CAMERA-BASED DETERMINING OF ROUGHNESS FOR ADDITIVELY MANUFACTURED COMPONENTS
    Publication number: 20170266886
    Abstract: The invention relates to a method and a device for the additive manufacturing of components by the layer-by-layer joining of powder particles to one another and/or to an already created pre-product or substrate, via the selective interaction of the powder particles with a high-energy beam (13) to create a layer, wherein a formed layer (14) is captured using a camera (6), wherein a contour of the deposited layer (14) is determined from an image of the deposited layer captured by the camera (6), and wherein the roughness of the surfaces of the formed component is determined from the contour.
    Type: Application
    Filed: May 20, 2015
    Publication date: September 21, 2017
    Applicant: MTU Aero Engines AG
    Inventors: Thomas HESS, Georg SCHLICK, Alexander LADEWIG
  • Method and electrode for electrochemically processing a workpiece
    Patent number: 9764403
    Abstract: A method for electrochemically processing a workpiece surface using an electrode, which has at least one effective surface for processing the workpiece surface, and using an electrolyte, wherein the electrolyte is suctioned away from the effective surface. The invention further relates to an electrode, which has at least one electrolyte feed for supplying the electrolyte to the effective area and an electrolyte suctioning system for suctioning the electrolyte away from the effective area.
    Type: Grant
    Filed: April 6, 2011
    Date of Patent: September 19, 2017
    Assignee: MTU Aero Engines GmbH
    Inventors: Erwin Bayer, Roland Huttner
  • Turbomachine blade
    Patent number: 9765625
    Abstract: A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 ?m and/or at most 1.5 mm in at least one direction.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: September 19, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Frank Stiehler, Andreas Hartung
  • Blade cascade
    Patent number: 9765633
    Abstract: A blade cascade for a turbomachine, having a number of blades (11, . . . 14; 21, . . . 25; 31, . . . 37) which include a monocrystalline material, each blade having a crystal orientation value (|?|), which is dependent on a crystal orientation of the monocrystalline material of the blade; the crystal orientation values of first blades (11, . . . 14) being less than a first limiting value and the crystal orientation values of second blades (21, . . . 25; 31, . . . 37) being at least equal to the first limiting value; and the blade cascade having at least one first sector (1), which includes at least three successive first blades (14, 12, 11, 13), and having at least one second sector (2+3; 2?+3?; 2?+3?), which includes at least three successive second blades (22, 21, 23, 24, 25; 31, 34, 36, 37, 33, 32, 35).
    Type: Grant
    Filed: December 9, 2014
    Date of Patent: September 19, 2017
    Assignee: MTU Aero Engines AG
    Inventor: Andreas Hartung
  • Process for producing a TiAl guide vane ring for a gas turbine and a corresponding guide vane ring
    Patent number: 9765632
    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: Grant
    Filed: August 8, 2013
    Date of Patent: September 19, 2017
    Assignee: MTU AERO ENGINES AG
    Inventor: Karl-Hermann Richter
  • Mid-frame for a gas turbine and gas turbine
    Patent number: 9759231
    Abstract: The invention relates to a mid-frame (10) for a gas turbine, having at least one outer casing element (12) and having a plurality of duct segments (16), which are arranged in succession in the radial direction on the inside of the outer casing element (12) and in the peripheral direction of the casing element (12) and by which segments, in each case, at least one duct (18) through which a gas can flow is delimited at least in the radial direction at least partially, wherein a ring element (22) that is common to the duct segments (16) and is formed in one piece is provided, by means of which the duct segments (16) are held at the outer casing element (12).
    Type: Grant
    Filed: May 18, 2015
    Date of Patent: September 12, 2017
    Assignee: MTU AERO ENGINES AG
    Inventors: Daniel Kirchner, Alois Eichinger
  • Method for fastening a brush sealing element in a groove of a housing segment
    Patent number: 9759077
    Abstract: A sealing system and method is disclosed. The sealing system includes a brush sealing element and an accommodating element with an accommodating chamber. The brush sealing element is disposed in the accommodating chamber and a bendable strap is disposed on the accommodating element. The method includes fastening the brush sealing element in the accommodating chamber of the accommodating element. The accommodating element is arranged in a groove of a housing segment and a position of the accommodating element is secured on the housing element by bending the strap of the accommodating element to engage with a side wall of the housing segment.
    Type: Grant
    Filed: April 29, 2011
    Date of Patent: September 12, 2017
    Assignee: MTU Aero Engines GmbH
    Inventors: Stefan Beichl, Erhan Uecguel
  • Component support and turbomachine
    Patent number: 9752455
    Abstract: A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: September 5, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Rudolf Stanka, Christoph Lauer, Hans Stricker
  • Method for operating an internal combustion engine
    Patent number: 9752528
    Abstract: A method and an arrangement for operating an internal combustion engine. In the method, an injection start is calculated by a filter, starting from a standard injection start and at least one of the filter parameters is selected in accordance with the operating mode of the internal combustion engine.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: September 5, 2017
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventor: Armin Dölker
  • Blade cascade and continuous-flow machine
    Patent number: 9745850
    Abstract: A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.
    Type: Grant
    Filed: May 23, 2014
    Date of Patent: August 29, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Yavuz Guendogdu, Jochen Gier, Karl Engel
  • Blade, integrally bladed rotor base body and turbomachine
    Patent number: 9739151
    Abstract: A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed.
    Type: Grant
    Filed: May 1, 2012
    Date of Patent: August 22, 2017
    Assignee: MTU Aero Engines GmbH
    Inventor: Frank Stiehler
  • Gas turbinen rotor blade
    Patent number: 9739156
    Abstract: A turbine or compressor stage of a gas turbine, the rotor blade having a radially outer shroud (1) which has a sealing fin array having a first sealing fin (3.1) and a second sealing fin (3.2) which is adjacent to the first sealing fin and connected thereto by a first groove base (10) having a circumferential region (13) of maximum radial height, which is located at a first circumferential position is provided. The sealing fin array has a third sealing fin (3.3) adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base (20) having a circumferential region (23) of maximum radial height, which is located at a second circumferential position different from the first circumferential position.
    Type: Grant
    Filed: November 21, 2014
    Date of Patent: August 22, 2017
    Assignee: MTU Aero Engines GmbH
    Inventors: Alexander Boeck, Sven Schmid
  • Low noise compressor and turbine for geared turbofan engine
    Patent number: 9733266
    Abstract: A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least a majority of the blade rows of the first turbine rotor, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60?5500, and the rotational speed being an approach speed in revolutions per minute.
    Type: Grant
    Filed: September 20, 2016
    Date of Patent: August 15, 2017
    Assignees: UNITED TECHNOLOGIES CORPORATION, MTU AERO ENGINES AG
    Inventors: David A. Topol, Bruce L. Morin, Detlef Korte