Patents Assigned to MTU
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Patent number: 10280775Abstract: The invention relates to a guide vane ring with at least one guide vane ring segment for a turbomachine, including a plurality of guide vanes arranged radially around an axis of rotation, an outer shroud arranged radially on the outer side of the guide vanes, and an inner shroud arranged radially on the inner side of the guide vanes, wherein the outer shroud or the inner shroud has at least one expansion joint, wherein the guide vane ring segment is formed in one piece with the guide vanes, the outer shroud, and the inner shroud and the at least one expansion joint is sealed in each case by at least one sealing device arranged in the respective expansion joint.Type: GrantFiled: January 26, 2016Date of Patent: May 7, 2019Assignee: MTU Aero Engines AGInventors: Christian Liebl, Richard Scharl, Daniel Kirchner, Alexander Buck, Thomas Hess
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Patent number: 10280934Abstract: The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point ? and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition ?>?1.33·ARax+5.16.Type: GrantFiled: August 24, 2016Date of Patent: May 7, 2019Assignee: MTU Aero Engines AGInventors: Werner Humhauser, Roland Matzgeller
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Patent number: 10285222Abstract: Disclosed is a method for generatively producing or for repairing at least one area of a component, wherein a zone arranged downstream of a molten bath is post-heated to a post-heating temperature and the component is set to a base temperature, and also a device for carrying out such a method.Type: GrantFiled: September 8, 2011Date of Patent: May 7, 2019Assignee: MTU AERO ENGINES AGInventors: Andreas Jakimov, Herbert Hanrieder, Wilhelm Meiners
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Publication number: 20190128130Abstract: A guide vane for a turbomachine is disclosed. The guide vane includes a heat pipe wall that is interpenetrated by a capillary system, which has a continuous material transition from a first surface, which delimits the guide vane toward the outside, to a second surface, which lies opposite to the first surface and delimits an evaporation cavity in the interior of the guide vane. Further disclosed is a method for producing a guide vane having a heat pipe wall, wherein at least the heat pipe wall is formed by additive manufacture.Type: ApplicationFiled: October 24, 2018Publication date: May 2, 2019Applicant: MTU Aero Engines AGInventor: Oliver Schmitz
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Publication number: 20190120061Abstract: The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.Type: ApplicationFiled: October 18, 2018Publication date: April 25, 2019Applicant: MTU Aero Engines AGInventors: Wolfgang Horn, Daniel Theurich, Martin Becker, Axel Stettner, Wilfried Schuette, Michael Junge, Hans-Peter Hackenberg, Alexander Halcoussis, Hannes Wolf
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Patent number: 10267157Abstract: The present invention relates to a rotating blade for a turbomachine, in particular a compressor stage or a turbine stage of a gas turbine, particularly of an aircraft engine, having a blade element for deflecting the flow, with a pressure side and a suction side, these sides being joined by a leading edge and a trailing edge, wherein a stacking axis of the blade element, in the radial direction over a radius r from a root of a blade element at r=0 to a tip of a blade element at r=H, has a course x(r) in a first downstream direction perpendicular to the radial direction and parallel to a principal axis of the turbomachine and has a course y(r) in a second direction perpendicular to the radial direction and to the first direction.Type: GrantFiled: October 19, 2016Date of Patent: April 23, 2019Assignee: MTU Aero Engines AGInventors: Kaspar Wolf, Klaus Wittig, Marcus Woehler, Martin Pernleitner, Wilfried Schuette
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Patent number: 10267167Abstract: Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. in the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.Type: GrantFiled: January 9, 2017Date of Patent: April 23, 2019Assignee: MTU Aero Engines AGInventors: Erich Steinhardt, Wilfried Smarsly, André Werner
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Patent number: 10265804Abstract: A method of producing holes in a component, in particular of turbomachines, wherein each hole extends from a first, outer surface to a second, inner surface of the component and wherein the method has, for example, the following steps: (i) producing a 3D model of the actual geometry of the component, at least for the region of the holes; (ii) adapting each hole on the basis of the actual geometry of the component; and (iii) generating a production program for each individual hole. In this way, the process quality and with it the quality of the holes increases, because the offset of holes caused by component tolerances is avoided and the drilling funnels are formed according to specification. Furthermore, drilling defects on account of the offset of holes and/or cores can be avoided. Overlapping holes caused by component tolerances are likewise avoided.Type: GrantFiled: February 26, 2015Date of Patent: April 23, 2019Assignee: MTU AERO ENGINES GMBHInventor: Josef Kriegmair
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Patent number: 10259042Abstract: The invention relates to a device for the manufacture or repair of a three-dimensional object, comprising at least one construction chamber for a successive solidification of at least one solidifiable material layer by layer in predefined regions for layer-by-layer buildup of the three-dimensional object or for layer-by-layer repair of individual regions of the three-dimensional object inside of the construction chamber, at least one coater that can travel for deposition of the material on at least one buildup and joining zone of a construction platform formed in the construction chamber, at least one inflow nozzle and at least one suction outlet nozzle for a process gas, with the inflow nozzle and the outlet nozzle being arranged in such a way that a gas flow that passes at least partially above the buildup and joining zone is created, and at least one overflow tank.Type: GrantFiled: January 22, 2016Date of Patent: April 16, 2019Assignee: MTU Aero Engines AGInventor: Maximilian Fisser
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Publication number: 20190101017Abstract: The present invention relates to a housing for a gas turbine compressor, having an operating duct for taking up several rows of rotating blades arranged one behind the other axially, wherein a wall of the operating duct has a first air bleed, wherein the housing has a cooling passage for cooling said operating duct wall by conveying air from the first air bleed to a first outlet passage for supplying at least one first bleed air consumer, wherein the first outlet passage is arranged downstream of the first air bleed, and wherein the operating duct wall has a second air bleed downstream of the first air bleed, and the housing has a discharge passage from said second air bleed to a second outlet passage for supplying at least one bleed air consumer.Type: ApplicationFiled: September 12, 2018Publication date: April 4, 2019Applicant: MTU Aero Engines AGInventor: Werner Humhauser
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Patent number: 10247005Abstract: A blade or vane arrangement for a turbomachine includes a turbomachine blade or vane and at least one tuning element guide housing with at least one cavity, in which at least one tuning element, which is provided for impact contact with the tuning element guide housing is taken up, the tuning element guide housing being arranged in a recess of the turbomachine blade or vane, wherein the cavity of the tuning element guide housing in which the tuning element is taken up, is closed in a gas-tight manner.Type: GrantFiled: November 6, 2015Date of Patent: April 2, 2019Assignee: MTU Aero Engines AGInventors: Andreas Hartung, Manfred Schill, Gerhard-Heinz Roesele
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Patent number: 10240474Abstract: A turbomachine includes a seal device for sealing a gap between two components, with a plurality of sealing elements tippable in the direction of a relative displacement of the components. The sealing elements are mounted on one of the components and bridge the gap where the device has prestressing elements, by which the tippable sealing elements are prestressed against a respective sealing edge of the components. The prestressing elements are each supported at a front support point and a back support point of the component on the mounting side, these points being distanced from one another in the axial direction and in the radial direction of the turbomachine where the front support point is disposed radially outside and the back support point is disposed radially inside with respect to the mounting.Type: GrantFiled: May 3, 2016Date of Patent: March 26, 2019Assignee: MTU Aero Engines AGInventors: Manfred Feldmann, Daniel Kirchner
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Patent number: 10240472Abstract: A brush seal for a turbomachine includes a support that has a recess, in which a spring element is clamped axially, which fastens a brush element, where the spring element is axially locked at an undercut in the recess.Type: GrantFiled: September 25, 2014Date of Patent: March 26, 2019Assignee: MTU Aero Engines AGInventor: Frank Stiehler
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Patent number: 10221797Abstract: A method and a control device for monitoring the pressure in a crankcase of an internal combustion engine. The desired values for the pressure in the crankcase are defined for a plurality of operating points of the internal combustion engine. Furthermore, at least one of the defined desired pressure values is modified during operation of the internal combustion engine.Type: GrantFiled: November 18, 2014Date of Patent: March 5, 2019Assignee: MTU FRIEDRICHSHAFEN GMBHInventors: Michael Hönl, Christian Rehm, Kai-Michael Trautz, Johannes Baldauf
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Patent number: 10221697Abstract: A turbine blade (100) having an airfoil (1). In its radially outer region, the turbine blade (100) has at least one shroud (200) or at least one shroud segment, as well as at least one cutting tooth (300) which is intended to engage at least once into portions of a turbine casing during use of the turbine blade (100). The cutting tooth (300) is connected to the shroud (200) or the shroud segment.Type: GrantFiled: December 10, 2013Date of Patent: March 5, 2019Assignee: MTU Aero Engines AGInventors: Alexander Boeck, Manfred Feldmann, Stephen Royston Williams
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Patent number: 10221744Abstract: A method for regenerating a particle filter during the operation of an internal combustion engine, having the following steps: detecting at least one loading parameter which is characteristic of a present loading of the particle filter, wherein an active regeneration measure can be carried out recurrently in a manner dependent on the loading parameter; determining a time window for a regeneration of the particle filter; and determining a prediction for an operating state of the internal combustion engine expected within the time window, wherein the active regeneration measure at a time indicated for it by the loading parameter is skipped if the prediction predicts that, within the time window, an operating state of the internal combustion engine will arise in which a regeneration of the particle filter takes place without an active regeneration measure.Type: GrantFiled: January 27, 2015Date of Patent: March 5, 2019Assignee: MTU FRIEDRICHSHAFEN GMBHInventor: Ralf Müller
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Patent number: 10215050Abstract: An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed.Type: GrantFiled: September 2, 2014Date of Patent: February 26, 2019Assignee: MTU Aero Engines AGInventors: Stefan Sasse, Norbert Schinko
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Patent number: 10208616Abstract: A turbomachine, particularly an aircraft engine, having a rotor, which is mounted rotatably around its longitudinal axis in a stator, and which has at least one row of rotating blades, which is formed by a plurality of rotating blades, is disclosed, wherein the stator has at least one abradable layer, and wherein each rotating blade has a blade tip that is lowered radially inward, at least in sections, proceeding from a leading edge on the side of the rotating blades in the direction of a trailing edge on the side of the rotating blades, and with a blade tip region that extends downstream from the leading edge runs into the abradable layer during operation of the turbomachine.Type: GrantFiled: June 26, 2015Date of Patent: February 19, 2019Assignee: MTU AERO ENGINES AGInventors: Axel Mattschas, Helmut Eibl, Sergio Elorza Gomez, Dirk Henrichs
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Patent number: 10208765Abstract: The present invention relates to an axial compressor for a gas turbine, in particular an aircraft engine, having at least one rotor blade or guide vane having a blade or vane element, which is arranged in a flow duct, and a leading edge and a trailing edge, which are joined to each other through a pressure side and a suction side, wherein, a new and novel profile section of the blade or vane element is provided.Type: GrantFiled: January 19, 2016Date of Patent: February 19, 2019Assignee: MTU Aero Engines AGInventors: Tobias Froebel, Sebastian Mann, Nina Wolfrum, Sergio Elorza Gomez
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Patent number: 10201875Abstract: 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: GrantFiled: December 11, 2017Date of Patent: February 12, 2019Assignee: MTU Aero Engines AGInventors: Christian Liebl, Steffen Schlothauer
