Patents Assigned to MTU Aero Engines GmbH
  • Patent number: 9657581
    Abstract: A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades (10a, 10b) having blade platforms (14a, 14b) engaged flush with one another, the blade ring including at least two groups of differently designed rotor blades (10a, 10b), each group of rotor blades (10a, 10b) being assigned blade platforms (14a, 14b), each of which is engageable flush with a matching blade platform (14a, 14b) of at least one other group of rotor blades (10a, 10b) and not with a blade platform (14a, 14b) of the same group of rotor blades (10a, 10b). A method for manufacturing a blade ring of a rotor for a turbomachine is also provided.
    Type: Grant
    Filed: January 22, 2013
    Date of Patent: May 23, 2017
    Assignee: MTU Aero Engines GmbH
    Inventors: Marcus Woehler, Martin Pernleitner, Rudolf Stanka
  • Patent number: 9624833
    Abstract: A compressor having a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, at least one clamping element bearing axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and being axially resiliently clamped between the inner ring and the seal carrier. A compressor with a clamping element for radial clamping is also provided.
    Type: Grant
    Filed: March 4, 2013
    Date of Patent: April 18, 2017
    Assignee: MTU Aero Engines GmbH
    Inventors: Juergen Kraus, Felix Kern
  • Patent number: 9550255
    Abstract: A method for depositing material layers on a workpiece made of a material which contains a titanium aluminide includes the steps of: preparing the workpiece; heating the workpiece in a localized region by induction to a predefined preheating temperature; and depositing an additive, preferably in powder form, on the heated surface of the workpiece by build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding; the additive including a titanium aluminide.
    Type: Grant
    Filed: June 16, 2011
    Date of Patent: January 24, 2017
    Assignee: MTU Aero Engines GmbH
    Inventors: Karl-Hermann Richter, Herbert Hanrieder, Sonja Dudziak, Albert Grueninger
  • Patent number: 9540946
    Abstract: A safety device (10) for a bearing arrangement of a rotor of a turbomachine, whereby the safety device (10) includes at least two support structures (12) between which at least one buckling structure (14) is arranged that is configured to collapse when a predetermined buckling load that acts on at least one of the support structures (12) is exceeded, thereby reducing the volume of the safety device (10). A method for the production of a safety device (10) for a bearing arrangement of a rotor of a turbomachine, as well as to a bearing arrangement of a rotor of a turbomachine having such a safety device (10).
    Type: Grant
    Filed: August 20, 2014
    Date of Patent: January 10, 2017
    Assignee: MTU Aero Engines GmbH
    Inventor: Alexander Boeck
  • Patent number: 9540953
    Abstract: A housing-side structure of a turbomachine, in particular of a gas turbine, including an in particular segmented jacket ring (16), which carries an abradable lining for radially outer ends of rotor-side moving blades of a moving blade ring, wherein the jacket ring (16) carrying the abradable lining is connected by means of at least one constriction (18) to a stator-side housing part (19), which is radially adjacent to the jacket ring (16) on the outside and the jacket ring is thermally decoupled from said stator-side housing.
    Type: Grant
    Filed: August 29, 2011
    Date of Patent: January 10, 2017
    Assignee: MTU Aero Engines GmbH
    Inventor: Wilfried Weidmann
  • Patent number: 9512512
    Abstract: A method for coating a component, in particular a component of a gas turbine or of an aircraft engine, is disclosed. The coating is applied to the component by kinetic cold gas spraying, where prior to the deposition of the coating, the surface of the component to be coated is cleaned and compacted by shot peening with a blasting media. A component produced in this manner is also disclosed.
    Type: Grant
    Filed: October 24, 2012
    Date of Patent: December 6, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Joachim Bamberg, Roland Hessert, Manuel Hertter
  • Patent number: 9506372
    Abstract: A damper (2) for damping a blade movement of a turbomachine (1), and to a method for producing the damper (2). The damper (2) has at least one side surface (21, 21?) which can be brought into frictional contact with a friction surface of the turbomachine (1) in order to damp a blade movement. The side surfaces (21, 21?) are asymmetrically convex in shape.
    Type: Grant
    Filed: November 29, 2011
    Date of Patent: November 29, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Carsten Schoenhoff, Manfred Dopfer, Martin Pernleitner, Wilfried Schuette
  • Patent number: 9492906
    Abstract: The invention relates to a method for cleaning a turbo-machine stage (100) consisting of at least one of the following steps: a cleaning nozzle (1) is introduced into an opening of a turbo-machine, in particular into an inspection opening (220); and the blade (100) of the stage is acted upon by solid particles, said particles subliming at the blade temperature, in particular into dry ice particles.
    Type: Grant
    Filed: August 3, 2011
    Date of Patent: November 15, 2016
    Assignee: MTU AERO ENGINES GMBH
    Inventors: Jürgen Rösing, Frank Seidel, Lutz Winkler, Bernd Kriegl, Thomas Uihlein, Martin Dürr, Fabian Moritz
  • Patent number: 9482099
    Abstract: The invention relates to a blade (2) of a turbomachine, in particular a rotor blade of a gas turbine, which has a variable transition radius (Rv1) in the vicinity of at least one platform overhang (16), and to a turbomachine having at least one such blade (2).
    Type: Grant
    Filed: January 14, 2011
    Date of Patent: November 1, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Markus Schlemmer, Bartlomiej Pikul
  • Patent number: 9470099
    Abstract: A securing device (20) for axially securing a blade root (12) of a blade in a groove (11) of a turbine engine. The outer contour (24) of the securing device (20) that faces a groove wall, in particular a groove base (33), is curved at least in some regions, the outer contour (24) having three different radii (R1, R2, R3) in some regions.
    Type: Grant
    Filed: November 11, 2011
    Date of Patent: October 18, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Rudolf Stanka, Manfred Dopfer, Martin Pernleitner, Wilfried Schuette
  • Patent number: 9470091
    Abstract: A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.
    Type: Grant
    Filed: February 6, 2013
    Date of Patent: October 18, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Sergio Elorza Gomez, Alexander Hergt, Ulrich Siller, Tim Schneider
  • Patent number: 9453423
    Abstract: A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.
    Type: Grant
    Filed: February 6, 2013
    Date of Patent: September 27, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Sergio Elorza Gomez, Tim Schneider
  • Patent number: 9453415
    Abstract: A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one suction-side depression that, in the circumferential direction, is at a distance from a suction-side wall, and having a section located upstream from the leading edges and a section located downstream from the leading edges, it has a pressure-side elevation that makes a transition to a pressure-side wall and that is located in a front blade area, and it has a pressure-side depression that is located upstream from the pressure-side elevation, and also discloses a continuous-flow machine having such a blade cascade.
    Type: Grant
    Filed: July 31, 2013
    Date of Patent: September 27, 2016
    Assignee: MTU Aero Engines GmbH
    Inventor: Karl Engel
  • Patent number: 9441490
    Abstract: A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension.
    Type: Grant
    Filed: October 4, 2012
    Date of Patent: September 13, 2016
    Assignee: MTU Aero Engines GmbH
    Inventor: Joerg Frischbier
  • Patent number: 9441786
    Abstract: Disclosed is a device for preserving fluid systems, for example of a fuel system and an oil system of a turbine engine, with at least one drive for driving at least one fuel pump and at least one oil pump, wherein a valve arrangement is provided, which makes transfer-pumping a fluid between the fluid systems possible, an engine having such a device as well as a method for triggering such a device or for preserving fluid systems.
    Type: Grant
    Filed: March 31, 2011
    Date of Patent: September 13, 2016
    Assignee: MTU AERO ENGINES GMBH
    Inventor: Helmut Streifinger
  • Patent number: 9435207
    Abstract: A blade for a blade row of a turbomachine having wired sections, in particular a blade of a compressor rotor blade, as well as a method for wiring sections of such a blade, is disclosed. Sections of a blade are wired in such a way that a first central component of a second section is selected according to at least one central component of a first section.
    Type: Grant
    Filed: January 29, 2011
    Date of Patent: September 6, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Sergio Elorza Gomez, Peter Eibelshaeuser
  • Patent number: 9435216
    Abstract: A sealing arrangement (100) in an axial turbomachine between, on the one hand, a rotor (1) and, on the other hand, a stator (3) and/or a housing, including a support device (7, 7?) and a sealing element, whereby the support device (7, 7?) extends essentially in the radial direction (r). In the axial direction (u) of the turbomachine, the support device (7, 7?) has an axial contour that effectuates a stiffening effect for the support device (7, 7?).
    Type: Grant
    Filed: September 2, 2014
    Date of Patent: September 6, 2016
    Assignee: MTU Aero Engines GmbH
    Inventor: Frank Stiehler
  • Patent number: 9404368
    Abstract: A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed.
    Type: Grant
    Filed: February 1, 2013
    Date of Patent: August 2, 2016
    Assignee: MTU Aero Engines GmbH
    Inventor: Roland Wunderer
  • Patent number: 9399924
    Abstract: A component, in particular for a gas turbine, is disclosed. The component has at least two component segments which are arranged relative to one another leaving a gap and are sealed against each other by a sealing device. The sealing device includes at least one brush seal. Also disclosed is a gas turbine, in particular an aircraft engine, having such a component.
    Type: Grant
    Filed: September 21, 2012
    Date of Patent: July 26, 2016
    Assignee: MTU Aero Engines GmbH
    Inventor: Hermann Klingels
  • Patent number: 9399918
    Abstract: A blade for a continuous-flow machine is disclosed, especially an aircraft engine, whereby, starting from the middle section, the cross section of the blade tip is reduced with respect to the middle section, at least over a front partial section in the direction of the leading edge and over at least a rear section in the direction of the trailing edge, and a continuous-flow machine having at least one row of blades including such blades is also disclosed.
    Type: Grant
    Filed: August 8, 2013
    Date of Patent: July 26, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Johann Geppert, Peter Eibelshaeuser, Heinz Rauschmair