Patents Assigned to MTU Aero Engines GmbH
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Publication number: 20130028749Abstract: A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial direction, and the centers of gravity of the blade sections extend along a stacking axis. The blade sections are stacked one on top of the other in the radial direction in such a way that, in a radially inner section of the blade adjacent to a radially outer section of the blade, the stacking axis has its single inflection point in its radial curvature, namely, between a first, radially inner subsection of the radially inner section in which the stacking axis has a concave curvature toward the pressure side, and a second, radially outer subsection of the radially inner section in which the stacking axis has a concave curvature toward the suction side.Type: ApplicationFiled: April 7, 2011Publication date: January 31, 2013Applicant: MTU Aero Engines GmbHInventor: Sergio Elorza Gomez
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Patent number: 8360302Abstract: The invention relates to a method for producing integrally bladed gas turbine rotors, especially of integrally bladed turbine rotors, wherein rotating blades (10) are joined to a rotor base (11) with the intermediate disposal of an adapter (14) in such a way that first an adapter is joined to a connecting section (15) of each rotating blade to be connected to the rotor base, and that subsequently each rotating blade (10) is joined to a connecting section (16) of rotor base (11) via adapter (14) connected to said blade. According to the invention, each adapter (14) is connected to connecting section (15) of the respective rotating blade (10) by welding, each rotating blade (10) being connected to the respective connecting section of the rotor base by inductive high-frequency pressure welding via adapter (14) connected to the blade.Type: GrantFiled: November 5, 2009Date of Patent: January 29, 2013Assignee: MTU Aero Engines GmbHInventor: Karl-Hermann Richter
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Patent number: 8360717Abstract: A blade of a turbomachine, in particular of a gas turbine, is disclosed. The blade includes at least one fastening section for fastening the same in a locating section of a rotor-side or stator-side component of the turbomachine. The, or each, fastening section has a core region which is made of a relatively brittle and relatively light material and is embedded in an encasing region made of a material having relatively high ductility.Type: GrantFiled: November 8, 2006Date of Patent: January 29, 2013Assignee: MTU Aero Engines GmbHInventor: Bernd Kriegl
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Patent number: 8356741Abstract: The invention relates to a method for producing a blade tip plating (20) on a blade (10) for a turbomachine, in particular on a high-pressure rotating compressor blade for a gas turbine, comprising the following steps: —producing a particle composite material (24) having embedded hard material particles (18); —placing the panicle composite material (24) on a solder (30) applied to the blade tip (16); and—healing the solder (30).Type: GrantFiled: February 2, 2010Date of Patent: January 22, 2013Assignee: MTU Aero Engines GmbHInventors: Thomas Uihlein, Erich Steinhardt, Werner Humhauser
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Patent number: 8354036Abstract: A method for the pre-treatment of titanium components for the subsequent coating thereof is provided. The method includes at least the following steps: a) etching of the component in an acidic solution containing fluoride and nitric acid (HNO3); b) activation pickling of the etched component in a solution containing at least sodium nitrate (NaNO3) and tetrafluoroboric acid (HBF4); and c) activation of the activation-pickled component in a bath containing acid or in an acidic bath containing nickel.Type: GrantFiled: November 14, 2006Date of Patent: January 15, 2013Assignee: MTU Aero Engines GmbHInventors: Helena Catalan-Asenjo, Michael Scheid, Josef Linska, Matthias Schmidt
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Patent number: 8347498Abstract: A method for repairing a guide vane segment of a gas turbine, the guide vane segment including at least two guide vanes as well as an inner and an outer shroud. At least one guide vane is irreparably damaged and is separated from the guide vane segment while the guide vane segment is completed by joining at least one replacement vane. If the one irreparable guide vane is located in one half of the segment outside the circumferential center of the guide vane segment, or if the several irreparable guide vanes are located in the same half of the segment, the matching number of guide vanes to be separated from the segment and replacement vanes to be joined to the segment are determined first. The determined number of replacement vanes are then joined to the guide vane segment. The same number of guide vanes, including the at least one irreparable guide vane, are finally separated from the guide vane segment.Type: GrantFiled: March 29, 2007Date of Patent: January 8, 2013Assignee: MTU Aero Engines GmbHInventor: Anja Lange
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Patent number: 8346383Abstract: The present invention relates to a method for determining a selected machining quality of components in a manufacturing process, particularly during metal cutting, having at least the following method steps of determining process-relevant variables by sensors and/or from the data stream in the machine controller, extracting variable curves characteristic for the respective machining process, selecting a number of different characteristics of the extracted variable curves, the linking of which enables a clear assignment to the selected machining quality, and multivariate linking of the selected characteristics to a characteristic pattern correlating with the selected machining quality.Type: GrantFiled: February 5, 2009Date of Patent: January 1, 2013Assignee: MTU Aero Engines GmbHInventors: Martin Eckstein, Günter Breitkopf, Rolf Kneilling
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Patent number: 8341841Abstract: A method for machining components of a gas turbine, in particular for machining turbine blades, is described. The method includes the following steps: a) providing at least one component carrier having at least one component receptacle for detachable accommodation and fastening component to be machined, the component receptacle being designed with a contour similar to at least one contour of subarea of component to be accommodated; b) introducing at least one subarea of the component into component receptacle and form-fitting and/or substance-to-substance bonding of the subarea of the component to component receptacle; c) machining the component, which is attached to the component carrier; and d) releasing the machined component from the component carrier.Type: GrantFiled: May 2, 2008Date of Patent: January 1, 2013Assignee: MTU Aero Engines GmbHInventor: Martin Fessler-Knobel
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Patent number: 8333553Abstract: The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades (11, 12; 12, 13; 13, 14) are permanently connected to each other within each guide blade segment (10) of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.Type: GrantFiled: February 14, 2008Date of Patent: December 18, 2012Assignee: MTU Aero Engines GmbHInventors: Christian Liebl, Hans-Georg Lottprein
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Publication number: 20120315148Abstract: The invention relates to a method for wiring suctions ((i), (i+1)) of a blade (1) for a blade row of a turbomachine. According to said method, a first central component (formula (II)) of a second section ((i+1)) is selected according to at least one central component ((formula (IV)), xCG(i), rCG(i)) of a first section ((i)), especially according to a formula (I) where: (i) is a variable of the first section; (i+1) is a variable of the second section; (formula (III)) is a central component of a section in the peripheral direction, preferably in the angular or radian measure; xCG is a central component of a section in the axial direction; rCG is a central component of a section in the radial direction; ? is a graduated angle of a section; and (formula (V)) is a peripheral incline, preferably in the angular or radian measure.Type: ApplicationFiled: January 29, 2011Publication date: December 13, 2012Applicant: MTU Aero Engines GmbhInventors: Sergio Elorza Gomez, Peter Eibelshaeuser
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Patent number: 8309232Abstract: A running-in coating for gas turbines and a method for production of a running-in coating are provided. The running-in coating serves to seal a radial gap between a housing (11) of the gas turbine and the rotating blades (10) themselves, whereby the running-in coating (13) is applied to the housing. The running-in coating is made from a CoNiCrAIY-hBN material. The CoNiCrAIY-hBN material can be applied by thermal spraying, in particular plasma spraying.Type: GrantFiled: November 12, 2004Date of Patent: November 13, 2012Assignee: MTU Aero Engines GmbHInventors: Manfred A. Daeubler, Klaus Schweitzer
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Publication number: 20120282098Abstract: A sealing device for an integrally bladed rotor basic body of a turbomachine to suppress a gas exchange between a hot gas stream and a cooling air stream in the radial direction in contact areas of adjacent moving blades, including a plurality of sealing elements activatable by centrifugal force, which may be situated in the area of channels which extend from a high-pressure side to a low-pressure side and are peripherally delimited by the moving blades, an integrally bladed rotor basic body having such a sealing device, and a turbomachine having such an integrally bladed rotor basic body.Type: ApplicationFiled: May 1, 2012Publication date: November 8, 2012Applicant: MTU Aero Engines GmbHInventors: Frank Stiehler, Manuel Hein
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Publication number: 20120282109Abstract: A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed.Type: ApplicationFiled: May 1, 2012Publication date: November 8, 2012Applicant: MTU Aero Engines GmbHInventor: Frank Stiehler
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Publication number: 20120282088Abstract: An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.Type: ApplicationFiled: May 1, 2012Publication date: November 8, 2012Applicant: MTU Aero Engines GmbHInventor: Frank Stiehler
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Publication number: 20120266439Abstract: 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: ApplicationFiled: April 6, 2012Publication date: October 25, 2012Applicant: MTU Aero Engines GmbHInventor: Peter GEIGER
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Patent number: 8286348Abstract: A method of forming integrally bladed rotors for gas turbines is described. The method includes drilling in a workpiece material recesses defining flow passages and rotor blades, performing a coarse milling step to refine surfaces of the rotor blades, and filling the recesses between the rotor blades with a damping material, thus encasing the rotor blades in the damping material. The method further includes performing a finishing milling step to remove the damping material and the workpiece material on surfaces of the rotor blades, while maximizing a damping effect of the damping material on the rotor blades. To maximize the damping effect, the finishing milling tool moves along a path that preferentially mills one surface of a blade while the other surface is in contact with the damping material.Type: GrantFiled: September 22, 2008Date of Patent: October 16, 2012Assignee: MTU Aero Engines GmbHInventors: Marjan Rozic, Dariusz Nowak, Derek Waszczuk
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Publication number: 20120251310Abstract: In a method for producing an inlet coating (21) on a surface of a turbomachine (10), an electric arc (37) is produced between a first electrode (31) having a first material and a second electrode (32) having a second material. A gas stream (42) is produced through the electric arc (37) onto the surface, which entrains the first material and the second material from the electric arc (37) and deposits them on the surface to form the inlet coating (21) or a precursor layer (22) of the inlet coating (21).Type: ApplicationFiled: October 30, 2010Publication date: October 4, 2012Applicant: MTU Aero Engines GmbHInventors: Wolfgang Wachter, Manuel Hertter
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Patent number: 8262897Abstract: The invention relates to a method for the production of aero-dynamic structures during the production of integrally bladed gas turbine rotors. Aerodynamic structures of an integrally bladed gas turbine rotor are produced on a rotor disk base body, whereon the end contours are precise, by removing material according to an electrochemical removal process, i.e. by means of an electrochemical machining (ECM)-process. The method comprises the following steps: a) preparing a rotor disk base body which is made of a material which is difficult to machine; b) removing the material which is between the blade wings until a specific dimension is obtained, according to a removal process; c) preparing at least one working electrode in order to finish at least one aerodynamic structure of an integrally bladed gas turbine rotor.Type: GrantFiled: July 25, 2005Date of Patent: September 11, 2012Assignee: MTU Aero Engines GmbHInventors: Erwin Bayer, Martin Bussmann, Thomas Kraenzler, Albin Platz, Juergen Steinwandel
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Patent number: 8262535Abstract: A planetary gear train is described which includes a sun gear, three or more planet gears, an annulus as well as a planet gear carrier, whereby the input is provided via the sun gear and the output is provided via the annulus or via the planet gear carrier, whereby each planet gear is mounted on both sides in a roller bearing, and whereby the planet gear carrier includes two axially spaced bearing washers as well as at least three webs that connect the bearing washers. Each roller bearing is configured as a single-row or multi-row cylindrical roller bearing, each planet gear has a flexurally elastic axis projecting axially on both sides beyond the gear body of the planet gear, and the connection between each roller bearing and the appertaining axis is configured to be spherically moveable.Type: GrantFiled: November 4, 2006Date of Patent: September 11, 2012Assignee: MTU Aero Engines GmbHInventor: Hermann Klingels
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Publication number: 20120225213Abstract: A method for spraying a coating and a cold gas spray nozzle is disclosed. The method includes spraying a coating by the cold gas spray nozzle. A rinsing gas is fed to the cold gas spray nozzle during an interruption of the spraying or at an end of the spraying. Deposits in the cold gas spray nozzle are cooled and detached by the rinsing gas.Type: ApplicationFiled: November 11, 2010Publication date: September 6, 2012Applicant: MTU Aero Engines GmbHInventors: Andreas Jakimov, Stefan Schneiderbanger, Manuel Hertter