Patents Assigned to MTU
  • Patent number: 10576581
    Abstract: An apparatus for laser materials processing including a laser (4) for generating a laser beam and a laser head (5) which is movable along at least one spatial direction and is connected to the laser via a light guide, and which emits a laser beam (7) capable of processing a material. The present invention also relates to an apparatus for selective laser melting or selective laser sintering having an apparatus for laser materials processing.
    Type: Grant
    Filed: October 16, 2018
    Date of Patent: March 3, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Christian Liebl, Steffen Schlothauer
  • Patent number: 10577948
    Abstract: The invention relates to a blade for use in a turbine of an aircraft engine. The blade is made of (a) a Mo-based alloy strengthened by intermetallic silicides or (b) a Ni-based single crystal superalloy. An aircraft engine and in particular, a turbofan aircraft engine including a corresponding turbine blade is also disclosed.
    Type: Grant
    Filed: October 29, 2015
    Date of Patent: March 3, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Wilfried Smarsly, Markus Fried, Thomas Goehler
  • Patent number: 10578127
    Abstract: Described is an adjustable guide vane ring of a turbomachine having an inner ring which is split radially and mounted axially together, on which a brush seal is configured, an inner ring for a guide vane ring of this kind, as well as a turbomachine.
    Type: Grant
    Filed: March 18, 2015
    Date of Patent: March 3, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Julian Weber, Alexander Griesmair
  • Patent number: 10570743
    Abstract: Disclosed is a turbomachine including a stator, a rotor rotatable about an axis of rotation, and an annulus for carrying a core flow, the annulus having a side wall on the stator and a side wall on the rotor, at least one airfoil array having a plurality of airfoils being disposed in the annulus. In a departure from an ideal aerodynamic annulus contour, a radial annulus enlargement begins upstream of the airfoils and extends downstream up to an aft portion of the airfoil array that follows the ideal aerodynamic annulus contour. Also disclosed is an airfoil for such a turbomachine.
    Type: Grant
    Filed: December 11, 2015
    Date of Patent: February 25, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Franz Malzacher, Markus Brettschneider
  • Patent number: 10570861
    Abstract: In a multi-fuel injector for an internal combustion engine, including a housing with a nozzle needle movably disposed therein between a closed position in which the nozzle needle blocks a discharge of fuel from a collection chamber, to which a first fuel is supplied, above the nozzle needle, a control chamber is arranged to which a high pressure second fuel is supplied which acts on the nozzle needle to bias it into a closed position, and a control valve is provided in a pressure release line extending from the control chamber for a controlled release of the second fuel from the control chamber by opening the control valve so as to relief the closing pressure on the nozzle needle in order to permit lifting of the nozzle needle from the closed position for discharging the fuel from the collection chamber.
    Type: Grant
    Filed: April 13, 2017
    Date of Patent: February 25, 2020
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Joachim Schwarte, Samuel Vogel, Robby Gerbeth
  • Patent number: 10570752
    Abstract: An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.
    Type: Grant
    Filed: May 5, 2017
    Date of Patent: February 25, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Gerhard-Heinz Roesele, Markus Schlemmer, Andreas Hartung
  • Publication number: 20200056499
    Abstract: The invention relates to a guide vane arrangement for a turbomachine, wherein the guide vane arrangement has a plurality of adjustable guide vanes that are rotatably mounted around an adjustment axis, at least one inner ring segment that is formed separately from the guide vanes, and a seal carrier that is formed separately from the at least one inner ring segment, wherein the at least one inner ring segment is fastened to one guide vane or to a plurality of guide vanes, and wherein the seal carrier is mounted in a spoke-centered manner with respect to the at least one inner ring segment, so that the seal carrier is movably mounted with respect to the at least one inner ring segment in the direction of at least one adjustment axis of at least one guide vane.
    Type: Application
    Filed: August 16, 2019
    Publication date: February 20, 2020
    Applicant: MTU Aero Engines AG
    Inventor: Frank Stiehler
  • Patent number: 10563568
    Abstract: A prechamber for an internal combustion engine, including a surface that is situated in the interior of the prechamber and that is impinged by a flow during the operation of the prechamber. The surface has at least one first surface region and at least one second surface region, wherein the first surface region has a defined texture, whereas the second surface region is untextured.
    Type: Grant
    Filed: October 6, 2016
    Date of Patent: February 18, 2020
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventor: Frederic Dumser
  • Patent number: 10563559
    Abstract: An exhaust gas aftertreatment system with an exhaust gas inlet, at least two exhaust gas aftertreatment elements, and a flow chamber. The exhaust gas inlet, the at least two exhaust gas aftertreatment elements, and the flow chamber are arranged relative to one another and fluidically connected together such that exhaust gas flowing through the exhaust gas inlet into the flow chamber can be distributed to the at least two exhaust gas aftertreatment elements. The exhaust gas passes through at least one first of the at least two exhaust gas aftertreatment elements along a first flow direction, and the exhaust gas passes through at least one second of the at least two exhaust gas aftertreatment elements along a second flow direction, wherein the first flow direction and the second flow direction are oriented at least diagonally to each other, preferably anti-parallel to each other.
    Type: Grant
    Filed: October 6, 2016
    Date of Patent: February 18, 2020
    Assignee: MTU FRIEDRICHSHAFEN GMBH
    Inventors: Mathias Bauknecht, Michael Engelhardt, Boban Maletic, Samuel Vogel
  • Patent number: 10563769
    Abstract: The invention relates to a method for manufacturing a brush seal with inclined bristles. In order to be able to manufacture these brush seals in an especially cost-effective manner, at least the following steps are provided: provision of a brush blank with at least one metal thread or wire packing fastened at or in at least one wire core; local, at least partial heating of at least the wire core and/or a subregion of the thread or wire packing adjacent to the wire core, by a current flow through the wire core; bending of the thread or wire packing relative to the wire core for producing of the inclined position of the bristles of the brush seal. The invention further relates to an apparatus for manufacturing brush seals and a brush seal for a turbomachine, in particular for an aircraft engine.
    Type: Grant
    Filed: January 6, 2017
    Date of Patent: February 18, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Alexander Gindorf, Joachim Bamberg, Guenter Zenzinger
  • Publication number: 20200047270
    Abstract: The present invention relates to a method for the production of drill holes in difficult to machine materials, in which a removal of material takes place in order to produce a drill hole by electrochemical erosion of material by an electrode that is moved in the longitudinal direction of the drill hole being produced in the direction onto the material to be processed at a feed rate, wherein the drilling has at least two steps, wherein, in the first step, the electrochemical processing takes place, and wherein, in a second step, the further processing of the drill hole to the final diameter takes place by machining processing or by erosion or by an electrochemical processing.
    Type: Application
    Filed: August 7, 2019
    Publication date: February 13, 2020
    Applicant: MTU Aero Engines AG
    Inventors: Albin Platz, Nicole Feiling, Anna Carina Kuepper, Norbert Huber
  • Patent number: 10550707
    Abstract: A seal system for a turbomachine, in particular a gas turbine, which includes a first component (10A, 10B), a second component (20), a flap (30) for sealing a gap between the first and second components, and a leaf spring, which includes a first leg (41) and a second leg (42), in a mounting state in which the flap and the second component do not contact each other, a projection of an abutment area (11) of the first component (10A, 10B), against which the first leg (41) is supported via the flap (30), is situated perpendicularly to a contact line (K) through at least two contact points of the first leg (41) with the flap (30), at least partially within a bearing surface (A) of the first component (10A, 10B), against which the second leg (42) of the pretensioned leaf spring is supported.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: February 4, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Alexander Boeck
  • Patent number: 10550720
    Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: February 4, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Publication number: 20200032884
    Abstract: A belt-tensioning device, in particular for an internal combustion engine, the belt-tensioning device including a bearing housing having a latching recess, a tensioning roller, a pivoting arm and a locking device. The pivoting arm is mounted on the bearing housing, the pivoting arm being under a torsion spring load. The tensioning roller being coupled to the pivoting arm. The locking device having a first latching device and a second latching device. The first latching device and the second latching device being coupled with the pivoting arm. The latching recess interacts with at least one of the first latching device and the second latching device wherein the locking device is configured in such a way that the pivoting arm can be locked by the locking device in different predefined latching positions and the pivoting arm can be pivoted with predefined freedom in an operating position.
    Type: Application
    Filed: October 3, 2019
    Publication date: January 30, 2020
    Applicant: MTU Friedrichshafen GmbH
    Inventor: Alexander Gross
  • Patent number: 10544697
    Abstract: The present invention relates to a process for producing a seal arrangement (1) for a turbomachine which comprises a seal support (2) and a stripping lining (3) which is arranged on the seal support, wherein the seal support comprises a fiber-reinforced plastic and the stripping lining comprises polysiloxane, and wherein the seal support and the stripping lining are prepared in a non-cured state and are arranged in direct contact with one another in accordance with the configuration of the seal arrangement, and are subsequently subjected to a common curing process such that fiber-reinforced plastic and polysiloxane cross-link with one another. The present invention further relates to a correspondingly produced seal arrangement and to a turbomachine having such a seal arrangement.
    Type: Grant
    Filed: September 19, 2014
    Date of Patent: January 28, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Siegfried Schmid, Michael Schober, Siegfried Sikorski, Axel Mattschas, Robert Bader
  • Patent number: 10544485
    Abstract: Disclosed is a process for producing a component from a TiAl alloy by layer-by-layer deposition of powder on a substrate and/or an already produced semifinished product. The component has a proportion of x at % of aluminum which is in the range from about 34 to about 47 at % of aluminum, the powder having a proportion of x+1 at % to x+6 at % of aluminum. Also disclosed is a component formed from a TiAl alloy which has been produced by a corresponding process.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: January 28, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Martin Schloffer, Wilfried Smarsly
  • Patent number: 10544687
    Abstract: The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The stiffening rib having substantially planar top surface in form of a trapezium, and two sloping sidewalls extending between the upstream sealing fin and the upstream edge on each side of the top surface and connecting said top surface with adjacent surface of the outer side of the shroud platform. The form of the stiffening rib allows to obtain an improved shroud configuration of reduced overall blade mass, capable of providing sufficient stiffening of the shroud, reducing vibrations of the shroud platform, creep curling of the shroud edges and bending stress at the intersection of the airfoil and of the shroud.
    Type: Grant
    Filed: July 10, 2017
    Date of Patent: January 28, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
  • Patent number: 10544689
    Abstract: A blade for a turbomachine comprising an outer shell and an inner core which is at least partially enclosed by the outer shell and has a higher porosity than the outer shell. The outer shell is formed by a ceramic body or a body made of a ceramic matrix composite material, and the inner core is formed by a fiber-reinforced ceramic or a fiber-reinforced ceramic matrix composite material.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: January 28, 2020
    Assignee: MTU AERO ENGINES AG
    Inventors: Artur Borto, Piotr Kapusta, Dawid Luczyniec
  • Patent number: 10544696
    Abstract: Disclosed is a sealing ring for a turbomachine, which is constructed so as to be fastened at a radially inner region of a plurality of guide vanes and rotate around a rotor shaft. The sealing ring comprises a ring part that extends in the axial direction and has a plurality of stiffened portions in succession in the peripheral direction. Further disclosed is a seal for a turbomachine that comprises such a sealing ring as well as a brush and/or run-in coating sealing ring that is to face a rotor shaft, and a method for the manufacture of a sealing ring.
    Type: Grant
    Filed: December 2, 2016
    Date of Patent: January 28, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Otto Liebscher, Oliver Thiele
  • Publication number: 20200024948
    Abstract: The present invention relates to a high pressure compressor for an engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.
    Type: Application
    Filed: July 22, 2019
    Publication date: January 23, 2020
    Applicant: MTU Aero Engines AG
    Inventors: Harsimar SAHOTA, Alexander HALCOUSSIS, Sergio ELORZA GOMEZ