Patents Assigned to MTU Aero Engines GmbH
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Patent number: 9399924Abstract: 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: GrantFiled: September 21, 2012Date of Patent: July 26, 2016Assignee: MTU Aero Engines GmbHInventor: Hermann Klingels
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Patent number: 9394597Abstract: A method for heat-treating gas turbine blades, namely for locally heat-treating at least one gas turbine blade in a blade section thereof; a blade root section, which is not to be heat-treated, of the gas turbine blade being positioned in a holding receptacle to prevent an unacceptable heating of the particular blade root section, which is not to be heat-treated, during the heat treatment of the particular blade section. The blade root section of the gas turbine blade is positioned in an interior space in a way that allows a remaining interior space of the holding receptacle, to be filled with a filler material; the holding receptacle, together with the gas turbine blade, being subsequently positioned in a heat treatment chamber to enable the gas turbine blade in the heat treatment chamber to undergo local heat treatment under vacuum.Type: GrantFiled: August 31, 2010Date of Patent: July 19, 2016Assignee: MTU Aero Engines GmbHInventors: Christian Hornig, Jens Weder
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Patent number: 9393622Abstract: A method for producing a thin-walled structural component from a casting material. The casting material is supplied as a powder, and the powder is deposited on a support (1) by a kinetic cold gas spraying process so as to form the structural component (11, 11?). A structural component which is made of a casting material and in which the structure is formed from a plurality of particles (17) that are interlinked and deformed using a cold gas spraying process.Type: GrantFiled: August 9, 2010Date of Patent: July 19, 2016Assignee: MTU Aero Engines GmbHInventors: Andreas Jakimov, Erwin Bayer, Karl-Heinz Dusel, Carsten Butz
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Patent number: 9382809Abstract: A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed.Type: GrantFiled: January 24, 2013Date of Patent: July 5, 2016Assignee: MTU AERO ENGINES GMBHInventors: Erwin Bayer, Thomas Hess, Manfred Feldmann, Sven Hiller, Peter Geiger
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Patent number: 9382916Abstract: A method for machining an integrally bladed rotor of a fluid-flow machine is disclosed. In accordance with an embodiment of the invention, the method includes the steps of: a) providing an integrally bladed rotor having a main rotor body and several rotor blades integrally attached to the main rotor body; b) determining the natural frequency of each rotor blade of the integrally bladed rotor; and c) machining at least one rotor blade of the integrally bladed rotor by removing material to adjust the natural frequency of the particular rotor blade to a specified value.Type: GrantFiled: February 4, 2006Date of Patent: July 5, 2016Assignee: MTU Aero Engines GmbHInventor: Harald Schoenenborn
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Patent number: 9382806Abstract: Intermediate housing (14), in particular of turbines (11, 13) of a gas turbine engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24?), having a crossflow channel (33), which is formed by the bounding walls (23, 24, 24?) and within which at least one supporting rib (15) is positioned that has a leading edge (16), a trailing edge (17), as well as side walls (18) extending between the leading edge (16) and the trailing edge (17) that direct a gas flow traversing the crossflow channel (33); the radially outer bounding wall (24) having a contour that changes in the circumferential direction at least in one section upstream of the supporting rib (15).Type: GrantFiled: January 16, 2012Date of Patent: July 5, 2016Assignee: MTU Aero Engines GmbHInventors: Martin Hoeger, Inga Mahle, Jochen Gier
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Publication number: 20160177774Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.Type: ApplicationFiled: January 27, 2015Publication date: June 23, 2016Applicant: MTU AERO ENGINES GMBHInventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Patent number: 9371733Abstract: In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade (1), the moving blade system having at least one cavity (3) in which at least one tuning mass (2) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall (3.1) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.Type: GrantFiled: November 5, 2011Date of Patent: June 21, 2016Assignee: MTU Aero Engines GmbHInventor: Andreas Hartung
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Patent number: 9364916Abstract: A method and device for producing a hole in an object is disclosed. The method includes the generation of a beam for removing material such that a bottom of a borehole is placed in a focus position of the beam, and a removal of material by impingement of the beam on the bottom of the borehole. A repeated placing of the bottom of the borehole in a focus position of the beam in order to compensate for the increased depth of the hole as a result of the removal of material is combined with a step of changing a radiation characteristic of the beam when the bottom of the borehole is repeatedly placed in a focus position.Type: GrantFiled: May 29, 2010Date of Patent: June 14, 2016Assignee: MTU Aero Engines GmbHInventors: Mark Geisel, Stefan Schur
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Patent number: 9359904Abstract: A blade for a turbomachine, in particular a jet engine, including a shroud, having two opposite lateral edges, for delimiting a main flow channel and including a blade which extends away from the shroud, a rounded transition area being provided which encompasses the blade on its root side and is guided beyond the one lateral edge, a section of the transition area protruding beyond the one lateral edge being severed and situated in the area of the other lateral edge as an elevation offset in the transverse direction, a blade arrangement having at least two of such blades as well as a turbomachine having a plurality of such blades.Type: GrantFiled: April 12, 2013Date of Patent: June 7, 2016Assignee: MTU Aero Engines GmbHInventors: Martin Pernleitner, Manfred Dopfer, Norbert Huebner
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Patent number: 9346141Abstract: A joining device for arranging a component on a component carrier is disclosed. The joining device includes an application system for positioning the component in the joining device and a receptacle for clamping the component carrier in the joining device. The component is arranged on the component carrier by an adapter. A method for arranging the component on the component carrier is also disclosed.Type: GrantFiled: July 7, 2010Date of Patent: May 24, 2016Assignee: MTU Aero Engines GmbHInventors: Martin Fessler-Knobel, Roland Huttner
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Patent number: 9333589Abstract: A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements.Type: GrantFiled: March 14, 2007Date of Patent: May 10, 2016Assignee: MTU Aero Engines GmbHInventors: Herbert Hanrieder, Alexander Gindorf, Reinhold Meier
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Patent number: 9333623Abstract: A method for removing a layer made of a first material from a surface of a body made of a second material is disclosed. The body is subjected to a pressurized jet containing a blasting medium composed of particles, where the pressurized jet at least intermittently has an Almen intensity of at most 0.35 Almen A, preferably at most 0.3 Almen A and particularly preferably at most 0.25 Almen A.Type: GrantFiled: August 6, 2011Date of Patent: May 10, 2016Assignee: MTU Aero Engines GmbHInventors: Horst Pillhoefer, Johann Oettl, Markus Niedermeier, Thomas Cosack, Dirk Ruhlig
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Publication number: 20160116442Abstract: The invention relates to a method of nondestructive and contactless testing of components (3), wherein ultrasonic waves (6) are irradiated onto the surface of the component (3) at a predefinable, non-perpendicular angle of incidence (9) using an ultrasonic transmission sound transducer (1) arranged spaced apart from the surface of the component (3) and the intensity of the ultrasonic waves (7) reflected from the surface of the component (3) is detected with time resolution and/or frequency resolution by the antenna array elements (2n) of an ultrasonic antenna array (2) configured for detecting ultrasonic waves (7) and the phase shift of the ultrasonic waves guided at the surface of the test body is determined therefrom with respect to the ultrasonic waves (7) directly reflected at the surface of the component (3).Type: ApplicationFiled: November 23, 2015Publication date: April 28, 2016Applicants: Fraunhofer-Gesellschaft Zur Foerderung Der Angewandten Forschung E.V., MTU Aero Engines GmbHInventors: Bernd KOEHLER, Martin BARTH, Joachim BAMBERG, Hans-Uwe BARON
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Patent number: 9322100Abstract: A method for manufacturing an abrasive coating on a gas turbine component, especially on a gas turbine rotor blade tip, comprising at least the following steps: a) providing a gas turbine component, especially a gas turbine rotor blade; b) providing a high temperature melting alloy powder; c) providing abrasive particles; d) providing a low temperature melting alloy powder; e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture; f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, especially to a tip of said turbine rotor blade; g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder is provided.Type: GrantFiled: May 4, 2007Date of Patent: April 26, 2016Assignees: MTU Aero Engines GmbH, Liburdi Engineering LimitedInventors: Karl-Heinz Manier, Ilya Chuprakov, Robert Sparling
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Patent number: 9322281Abstract: A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment surface. The stiffening structure is cross-shaped at least in some areas.Type: GrantFiled: June 21, 2010Date of Patent: April 26, 2016Assignee: MTU Aero Engines GmbHInventors: Markus Schlemmer, Bartlomiej Pikul
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Patent number: 9321107Abstract: A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.Type: GrantFiled: November 6, 2012Date of Patent: April 26, 2016Assignee: MTU Aero Engines GmbHInventors: Bernd Daniels, Herbert Hanrieder, Karl-Hermann Richter, Michael Strasser
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Patent number: 9314844Abstract: A method for manufacturing a component having at least one element configured in the component, in particular at least one conduit, conduit unit, or supporting element configured within an aerodynamic rib, the component having an element leadthrough for leading through the at least one element, the method including the following step: building up in layers of the component including the element leadthrough, together with the at least one element in a generative production process.Type: GrantFiled: April 6, 2012Date of Patent: April 19, 2016Assignee: MTU Aero Engines GmbHInventor: Peter Geiger
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Method and damping device for vibration damping of a blade of a turbomachine as well as turbomachine
Patent number: 9316116Abstract: A method for vibration damping of at least one blade of a turbomachine, wherein initially at least one damping element is arranged on the blade such that it can move in the axial direction, employs a damping element having a larger permeability constant than the blade (?rD>?rB), and then a magnetic field acting in the radial direction is generated at least temporarily during rotation of a rotor hub of the turbomachine in order to adjust the mass of the damping element in real time. A damping device includes, for example, a ferromagnetic damping element as well as a magnetic field source, and a turbomachine.Type: GrantFiled: January 17, 2013Date of Patent: April 19, 2016Assignee: MTU AERO ENGINES GmbHInventor: Ulrich Retze -
Patent number: 9316103Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.Type: GrantFiled: November 21, 2012Date of Patent: April 19, 2016Assignee: MTU AERO ENGINES GmbHInventors: Harald Passrucker, Roland Wunderer