Patents Assigned to MTU
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Patent number: 10436044Abstract: The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet engine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge, wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.Type: GrantFiled: December 2, 2016Date of Patent: October 8, 2019Assignee: MTU Aero Engines AGInventors: Markus Schlemmer, Martin Pernleitner, Nina Wolfrum, Markus Brettschneider, Inga Mahle
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Patent number: 10436052Abstract: A leaf seal for sealing off a shaft rotating around an axis, particularly in a gas turbine, is disclosed. The leaf seal includes a plurality of leaves arranged spaced apart from one another, where the leaves are produced integrally with a basic element supporting the leaves by a generative production process. A process for producing a leaf seal for sealing off a shaft rotating around an axis is also disclosed.Type: GrantFiled: July 30, 2015Date of Patent: October 8, 2019Assignee: MTU Aero Engines AGInventors: Julian Weber, Christoph Cernay, Thomas Hess
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Publication number: 20190299288Abstract: A method for producing a component from a TiAl alloy and a correspondingly produced component includes defining at least one first component region with a first property profile, and at least one second component region with a second property profile, which is different from the first property profile; providing a powder made of the TiAl alloy; additively manufacturing the component from the powder composed of the TiAl alloy, wherein the powder made of the TiAl alloy is melted for the cohesive binding of the powder particles to one another and to the substrate or to an already produced part of the component, and wherein the powder particles are melted for the formation of the first component region, and the powder particles for the formation of the second component region are melted under different conditions, so different chemical compositions of the deposited material are produced in both component regions.Type: ApplicationFiled: February 20, 2019Publication date: October 3, 2019Applicant: MTU Aero Engines AGInventor: Martin Schloffer
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Patent number: 10428668Abstract: The invention relates to a guide vane segment for an aircraft gas turbine, comprising at least a radially outer shroud and a radially inner shroud, which extend along a respective circular arc and together form a ring segment, wherein, in the radial direction, between the outer shroud and the inner shroud, a plurality of guide vanes are arranged next to one another in the peripheral direction (UR), the vanes being materially joined with the inner shroud and the outer shroud, in particular joined in one piece. At least two securing ribs are arranged next to one another are formed on the trailing end face for at least one guide vane, wherein an intermediate space delimited by the two securing ribs in the peripheral direction (UR) is formed, this space tapering from radially outside to radially inside.Type: GrantFiled: November 14, 2016Date of Patent: October 1, 2019Assignee: MTU Aero Engines AGInventors: Markus Schlemmer, Oliver Thiele, Bernd Kislinger, Wilfried Schuette, Manuel Hein
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Patent number: 10428656Abstract: The present invention relates to a gas turbine, in particular an aircraft engine gas turbine having a shaft and a bladed turbine rotor joined therewith that has a first rotor segment which has a downstream rotating cascade of the turbine rotor and bounds a first space in the radial direction, this first space communicating with a first gas passage disposed in the shaft, and has a second rotor segment axially adjacent to the first rotor segment, which has at least one second rotating cascade of the turbine rotor and bounds in the radial direction a second space axially adjacent to the first space, this second space communicating with a second gas passage, wherein the first rotor segment has at least one first discharge opening for the discharge of gas from the first space upstream of the furthest downstream rotating cascade.Type: GrantFiled: July 19, 2016Date of Patent: October 1, 2019Assignee: MTU Aero Engines AGInventors: Klaus Pirker, Christoph Lauer
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Patent number: 10427244Abstract: Disclosed is a method for generatively producing components by layer-by-layer building from a powder material by selective material bonding of powder particles by a high-energy beam. An eddy current testing is carried out concurrently with the material bonding. Also disclosed is an apparatus which is suitable for carrying out the method.Type: GrantFiled: July 8, 2014Date of Patent: October 1, 2019Assignee: MTU AERO ENGINES AGInventors: Andreas Jakimov, Georg Schlick, Joachim Bamberg, Thomas Hess
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Patent number: 10428437Abstract: Disclosed is process for producing a wear-resistant coating on a component. The process comprises providing an electrolyte which contains Co and/or Ni, dispersing first particles comprising hard material particles and/or slip material particles in the electrolyte, dispersing second particles comprising metal alloy particles in which the metal alloy comprises chromium and aluminum in the electrolyte, providing a component to be coated in a bath of the electrolyte which has first and second particles dispersed therein, and electrodepositing a matrix of Co and/or Ni with incorporated first and second particles on the component. A correspondingly produced wear-resistant coating is also disclosed.Type: GrantFiled: September 12, 2014Date of Patent: October 1, 2019Assignee: MTU AERO ENGINES AGInventors: André Werner, Josef Linska
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Publication number: 20190293550Abstract: A method for evaluating the quality of a component produced by means of an additive laser sintering and/or laser melting method, in particular a component for an aircraft engine, includes at least the steps of providing a first data set, which comprises spatially resolved color values, which each characterize the temperature of the component at an associated component location during the laser sintering and/or laser melting of the component, providing a second data set, which comprises spatially resolved color values corresponding to the first data set, which color values each characterize the temperature of a reference component at an associated reference component location during the laser sintering and/or laser melting of the reference component.Type: ApplicationFiled: June 10, 2019Publication date: September 26, 2019Applicant: MTU Aero Engines AGInventors: Thomas Hess, Gunter Zenzinger, Wilhelm Satzger
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Patent number: 10422247Abstract: The present invention relates to a turbomachine with a housing structure as well as a corresponding housing structure an outer housing wall and an inner housing wall, which, passing around the flow duct of the turbomachine at a distance from each other, surround the outer side of the flow duct, wherein the inner housing wall of the housing structure is formed by an OAS (outer air seal, outer fluid seal) in the region of the rotating blades of the turbomachine, which rotate around an axial axis of the turbomachine, wherein a heat protection shield is constructed between the outer housing wall and the OAS. The heat protection shield has a plurality of spacers in the peripheral direction that are distanced from one another in the peripheral direction and are situated additionally to and in the radial direction outside of the heat protection element.Type: GrantFiled: December 1, 2016Date of Patent: September 24, 2019Assignee: MTU Aero Engines AGInventors: Petra Kufner, Walter Gieg
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Patent number: 10422231Abstract: The present invention relates to a bladed rotor for a gas turbine, with a body and a plurality of rotating blades where contact regions of a cylindrical surface of the body and front faces of the rotating blades are joined together cohesively. At least one of these contact regions and/or at least one of these front faces has at least one blind hole, in which at least one impulse body is arranged with play of movement and which is sealed and rotating blades are joined with the cylindrical surface. Alternatively, the body and rotating blades are manufactured integrally with one another by machining, and at least one blind hole extends from an inner surface of the body facing away from the blade out to one of the rotating blades, at least one impulse body being disposed with play of movement in this hole, and this hole is sealed.Type: GrantFiled: August 8, 2016Date of Patent: September 24, 2019Assignee: MTU Aero Engines AGInventor: Andreas Hartung
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Publication number: 20190288624Abstract: There is disclosed a fault ride-through system for use in a power system comprising a synchronous generator driven by a prime mover. The fault ride-through system comprises a mechanical switch connected in parallel with a dynamic power dissipater, wherein the dynamic power dissipater comprises a solid-state switch connected in series with a braking resistor. A controller is configured to control the mechanical switch and the solid-state switch to control the current through the braking resistor, based on received data indicative of one or more operation parameters of the power system.Type: ApplicationFiled: February 19, 2019Publication date: September 19, 2019Applicants: ROLLS-ROYCE plc, MTU FRIEDRICHSHAFEN GMBH, MTU ONSITE ENERGY GMBHInventors: Amit K GUPTA, Johannes DEMHARTER, Yang SHICONG, Souvik DASGUPTA, Michael KREISSL, Abhisek UKIL
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Patent number: 10415425Abstract: The invention relates to a turbomachine including: a guide baffle, whose sv guide blades are situated on c guide blade carriers; and an adjacent moving baffle including sb moving blades; the guide baffle nv including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nb including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient ? i = 1 n v ? ? m i s v - c of sum ? i = 1 n v ? ? m i of the masses of all impulse bodies of the guide baffle divided by the difference (sv?c) of the number sv of all guide blades minus the number c of all guide blade carriers amounts to at least 1.Type: GrantFiled: January 17, 2017Date of Patent: September 17, 2019Assignee: MTU Aero Engines AGInventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
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Patent number: 10415430Abstract: A coupling assembly, including a first component and a second component overlapping in a join region; a joining device allowing the first and second components to rest against each other clampingly and region; the joining device including a clamp resting on the first component and the second component and having a bolt connection adapted for securing the clamp to the first and second component. The first and second components are manufactured from a ceramic matrix composite; the first component having a holding portion including a front side facing the clamp, a rear side facing away from the clamp, and a receiving opening; and the bolt connection having a bolt portion that extends through the receiving opening and, at the end thereof facing away from the clamp, having a bracing portion angled relative to the longitudinal axis of the bolt portion and that rests against the rear side.Type: GrantFiled: April 5, 2017Date of Patent: September 17, 2019Assignee: MTU Aero Engines AGInventor: Alexander Boeck
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Patent number: 10415400Abstract: A method for manufacturing a blade (1) for a turbomachine, the blade having a hardfacing on its tip (4) and an erosion-protection coating (13) at least on its airfoil (3) is provided. Initially, a blade tip hardfacing is applied to the blade tip and, subsequently, a mask (10) is positioned in the region of the blade tip hardfacing, the mask covering the blade tip hardfacing, and, subsequently, the erosion-protection coating is deposited. The mask is removed after the erosion-protection coating is completed. A blade for a turbomachine, the blade having a hardfacing on its tip (4) and an erosion-protection coating (13) at least on its airfoil (3) is also provided. The erosion-protection coating at least partially covers the blade tip hardfacing, and the thickness of the erosion-protection coating decreases continuously in and/or toward the region of the blade tip hardfacing.Type: GrantFiled: May 12, 2016Date of Patent: September 17, 2019Assignee: MTU Aero Engines AGInventors: Thomas Uihlein, Ralf Stolle
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Publication number: 20190275575Abstract: The present invention relates to a hydraulic extrusion tool for extruding a rotor shaft for a turbomachine, and a corresponding method. The turbomachine has a structure that is fastened to the rotor shaft by of a press fit. The extrusion tool has a first tool part that is configured for the purpose of being arranged on a first side of the structure, and which has a coupling mechanism that is configured for the purpose of coupling the first tool part to the structure, in such a way that the first tool part and the structure cannot move away from each other, at least in one direction along an axis of the rotor shaft; and an induction device that is configured for the purpose of heating the structure induction in the region of the press fit.Type: ApplicationFiled: March 5, 2019Publication date: September 12, 2019Applicant: MTU Aero Engines AGInventor: MTU Aero Engines AG
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Publication number: 20190277148Abstract: The invention relates to an inner ring for a guide vane assembly for mounting adjustable guide vanes of a turbomachine, of a compressor stage or turbine stage of a gas turbine, a guide vane assembly for a turbomachine having an inner ring, a turbomachine having an inner ring, and a method for producing an inner ring, wherein the inner ring has a plurality of guide vane bearing mounts, which are each arranged spaced apart in the peripheral direction, recesses, which are each formed for receiving a bearing element, in particular a bearing journal, of a guide vane, wherein, between at least two adjacent guide vane bearing mounts, the inner ring has at least one depression with a wall thickness in a radial direction that is reduced in comparison to a region that abuts the depression and is outside of the depression.Type: ApplicationFiled: March 6, 2019Publication date: September 12, 2019Applicant: MTU Aero Engines AGInventor: Lothar Albers
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Patent number: 10400613Abstract: The present invention relates to a method for producing a blade or blade arrangement of a turbomachine, which features the following steps: producing a blade (4) from at least one blade material, machining the blade in at least one region of the blade by a surface machining process, cleaning the surface of the blade depositing an erosion protection coating (10) of at least two layers of different hardness by physical vapor deposition in the at least one region, machining the erosion protection coating (10) by a coating smoothing process in order to establish a defined surface roughness. Furthermore, the invention relates to correspondingly produced blades or blade arrangements.Type: GrantFiled: May 19, 2017Date of Patent: September 3, 2019Assignee: MTU AERO ENGINES AGInventors: Joerg Windprechtinger, Ralf Stolle, Philipp Utz, Thomas Uihlein, Markus Gether
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Patent number: 10400611Abstract: The invention relates to a blade for a turbomachine a shroud for such a blade, and a turbomachine having at least one such blade. The blade comprises a shroud which is positioned on the blade tip side of the blade and is stiffened in the region of its surface by means of a stiffening structure having at least one longitudinal stiffening element such as a rib. The height of the longitudinal stiffening element varies in the circumferential direction.Type: GrantFiled: January 28, 2016Date of Patent: September 3, 2019Assignee: MTU AERO ENGINES AGInventors: Marcin Kozdras, Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
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Patent number: 10393160Abstract: Disclosed is a component with a component section and a flange that is arranged at the component section for connection of the component another element. Arranged at the flange is one or a plurality of oblique flange channels, that is, channels for respectively accommodating a section of a connection element that runs obliquely to a surface portion of the component section that lies opposite to the flange. Further disclosed is a flange connection with at least one component of this kind, another component, and at least one connection element. Disclosed, in addition, is a turbomachine with a housing that is assembled from two or more components by means of such a flange connection.Type: GrantFiled: March 13, 2018Date of Patent: August 27, 2019Assignee: MTU Aero Engines AGInventors: Hermann Klingels, Wolfgang Bickmeier
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Patent number: 10392972Abstract: A liner element of a hot-gas-conveying duct of a turbine intermediate case of a gas turbine, in particular of an aircraft gas turbine, the liner element includes a central portion having at least one first reinforcement portion projecting in a direction away from the duct and extending substantially straight between an axial forward end and an axial rearward end; at least one of the two axial ends being adjoined by a second reinforcement portion projecting in a direction away from the duct and extending inclinedly or curvedly relative to the straight-line extent of the first reinforcement portion; the first reinforcement portion and the second reinforcement portion together forming a reinforcing element; the entire reinforcing element being disposed within the outer surface of the central portion, in particular in such a way that the reinforcing element is spaced apart from the first connecting portion and from the second connecting portion.Type: GrantFiled: July 19, 2017Date of Patent: August 27, 2019Assignee: MTU Aero Engines AGInventors: Thomas Flatscher, Alois Eichinger, Wolfgang Bickmeier, Manfred Feldmann, Daniel Kirchner, Johannes Geisler