Patents Assigned to MTU Aero Engines GmbH
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Publication number: 20100186472Abstract: A method and device for surface peening, particularly ultrasonic shot peening, of a component in the region of a passage opening is disclosed. A vibration device impinging the blasting material is disposed on one side and a counter-element is disposed on an opposite side relative to a component region having the passage opening. The counter-element is disposed at a distance relative to the corresponding side of the component region.Type: ApplicationFiled: June 6, 2008Publication date: July 29, 2010Applicant: MTU Aero Engines GmbHInventors: Erwin Bayer, Eggert Reese, Juergen Steinwandel
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Patent number: 7758297Abstract: A method for flow optimization in multi-stage turbine-type machines in which the inflow of a third of three consecutive blade rings is optimized, the first and the third blade ring having the same number of blades being situated on the same unit, rotor or stator, the second blade ring being situated on the other of the two units, rotor or stator, and an operating state, occurring during a high proportion of the operating time, being selected by ascertaining or predefining the appropriate operating parameters. In this operating state, the maxima of the obstruction, periodically occurring in the area of the outlet edges of the blade profiles of the second blade ring, are deflected onto the inlet edges of the blade profiles of the third blade ring within a predefined tolerance angle; the positions or the geometries of blade profiles of at least one of the three blade rings are modified as needed.Type: GrantFiled: May 10, 2006Date of Patent: July 20, 2010Assignee: MTU Aero Engines GmbHInventor: Andreas Fiala
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Patent number: 7757927Abstract: Two structural components, such as a gas turbine rotor hub and a rotor blade, are integrally joined to each other by friction welding, particularly linear friction welding. For this purpose, each component is provided with a joining surface and at least one of the two components is provided with a groove next to the respective joining surface. The groove extends fully or partly around the respective joining surface and serves for reducing stress in a normal and radial direction of the respective joining surface, whereby a more uniform heating of the joining zone is achieved and joining faults are avoided or at least reduced during the friction welding.Type: GrantFiled: June 8, 2006Date of Patent: July 20, 2010Assignee: MTU Aero Engines GmbHInventor: Joachim Bamberg
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Patent number: 7758301Abstract: A gas turbine machine includes a second turbine (11), e.g. a low pressure turbine, positioned downstream from a first turbine (10), e.g. a medium pressure turbine. An arrangement for detecting a shaft break of a rotor shaft includes an operator element (16) positioned between the rotor of the first turbine (10) and a stator of the second turbine (11) radially inwardly relative to a flow channel, and a sensor element (21) guided in the stator of the second turbine (11), to convert a shaft break, detected by the radially inwardly positioned operator element (16), into an electrical signal and to transmit this electrical signal to a switching element which is positioned radially outwardly relative to the flow channel on a housing of the gas turbine machine.Type: GrantFiled: July 7, 2005Date of Patent: July 20, 2010Assignee: MTU Aero Engines GmbHInventors: Christopher Bilson, Ian Fitzgerald
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Publication number: 20100173094Abstract: 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: ApplicationFiled: May 4, 2007Publication date: July 8, 2010Applicants: MTU Aero Engines GmbH, Liburdi Engineering LimitedInventors: Karl-Heinz Manier, Llya Chuprakov, Roberto Sparling
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Publication number: 20100166944Abstract: A method for determining the polyester fraction in a multi-component powder during a thermal spraying process is disclosed. The multi-component powder is heated and fed to an object with the aid of a carrier, forming a coating on the object. At least one measured value for the intensity of the light emitted by the combination of the carrier and multi-component powder material on the way to the object is detected at least in the range of a characteristic wavelength of polyester. A characteristic value is derived from the combination of the measured values, and the fraction of the polyester to be determined is calculated on the basis of a previously determined relationship between the characteristic value and the polyester fraction.Type: ApplicationFiled: November 2, 2007Publication date: July 1, 2010Applicant: MTU Aero Engines GmbHInventors: Andreas Jakimov, Manuel Hertter, Andreas Kaehny
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Publication number: 20100169048Abstract: A maintenance planning method for turbomachines, especially for gas turbine aircraft engines, is disclosed. In an embodiment, the method includes: a) data obtained from the previous maintenance of turbomachines is stored in a database in a structured manner, where the data especially correlates maintenance work carried out with operating loads of a serviced turbomachine; b) in order to pre-plan the maintenance of a turbomachine undergoing further maintenance, the maintenance work to be carried out is planned in terms of type and sequence on the basis of the database; and c) the turbomachine undergoing further maintenance is inspected for the final planning of the maintenance, and the type and/or sequence of the maintenance work to be carried out, which was specified during the pre-planning of the maintenance, is adapted and/or supplemented on the basis of the inspection.Type: ApplicationFiled: September 7, 2007Publication date: July 1, 2010Applicant: MTU Aero Engines GmbHInventors: Klaus Hanreich, Rolf Burmeister, Torsten Petrick, Ferdinand Exler
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Patent number: 7743639Abstract: A method and a device are for testing the detectability of at least one flaw in a component, or for evaluating ultrasonic signals of the flaw. The method provides for an electronic specification of the flaw to be generated, which includes a two-dimensional or three-dimensional point pattern. This specification predefines the number, position, shape, orientation, and dimensions of flaws to be deliberately generated. A test specimen is produced, where for each point of the point pattern, a microcrack is generated at the position of this point. An ultrasonic image of the test specimen is recorded and evaluated. The test specimen may be made out of a material transparent to visible light, e.g., crown glass, optical glass, borosilicate glass, or quartz glass. The microcracks may be produced, using internal laser engraving.Type: GrantFiled: November 9, 2004Date of Patent: June 29, 2010Assignee: MTU Aero Engines GmbHInventors: Joachim Bamberg, Wolf-Dieter Feist
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Publication number: 20100158691Abstract: 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: ApplicationFiled: March 14, 2007Publication date: June 24, 2010Applicant: MTU Aero Engines GmbHInventors: Herbert Hanrieder, Alexander Gindorf, Reinhold Meier
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Patent number: 7735712Abstract: A rotary friction welding machine and method is disclosed. The rotary friction welding machine has a first rotating spindle and a second non-rotating spindle, where a first component of the components being connected to one another is positioned on the first spindle and a second component of the components being connected to one another is positioned on the second spindle. Several flywheel mass bodies are positioned on the rotary friction welding machine, where the flywheel mass bodies cooperate with the first rotating spindle such that at least one of these flywheel mass bodies can be brought out of operating engagement or into operating engagement with the first rotating spindle, where both the flywheel mass bodies that are in operating engagement with the first rotating spindle and the flywheel mass bodies that are out of operating engagement with the first rotating spindle are positioned on the rotary friction welding machine.Type: GrantFiled: March 4, 2005Date of Patent: June 15, 2010Assignee: MTU Aero Engines GmbHInventors: Karsten Dzialas, Thomas Sparks
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Patent number: 7736732Abstract: A method for producing an erosion-resistant protective coating is disclosed. At least one lacquer material is provided wherein the lacquer material is a phosphate or silicate mixed with particles. Then, at least one layer of the lacquer material or each lacquer material is applied to a component that is to be protected from erosion. Then the applied lacquer layer or each applied lacquer layer is converted to a glass layer.Type: GrantFiled: June 19, 2004Date of Patent: June 15, 2010Assignee: MTU Aero Engines GmbHInventors: Erwin Bayer, Gerhard Wydra
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Patent number: 7735310Abstract: A gas turbine, such as an aircraft engine, has at least one compressor, at least one turbine, a combustion chamber, and a fuel pump to supply fuel to the combustion chamber. Upon identification of a break of a shaft that couples a compressor with a turbine, the gas turbine is shut off. For this purpose, at least one electrical current conductor is arranged on the shaft, whereby this current conductor is a component of a current supply for the fuel pump or for a fuel pump regulation. When the integrity of the current conductor is disrupted, thereby the current supply of the fuel pump or of the fuel pump regulation is interrupted in order to automatically shut off the gas turbine.Type: GrantFiled: September 17, 2005Date of Patent: June 15, 2010Assignee: MTU Aero Engines GmbHInventor: Martin Metscher
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Publication number: 20100143100Abstract: Jet engine (1), especially for an aircraft, with at least one hollow shaft (7) and/or low pressure shaft (8) rotatably supported in at least one bearing arrangement about a center axis, on which shaft at least respectively one high and/or low pressure compressor (2, 12) as well as at least respectively one high and/or low pressure turbine is arranged, whereby the jet engine (1) further comprises an electromechanical unit (10), in order to provide at least a motor function for starting the jet engine (1) and/or a generator function for the power supply, whereby the electromechanical unit (10) is arranged centrally about the center axis, whereby the electromechanical unit (10) furthermore encompasses the function of an active magnetic bearing arrangement, in order to form at least one bearing arrangement of the at least one hollow shaft (7) and/or low pressure shaft (8), and whereby the electromechanical unit (10) is embodied as a transverse flux machine.Type: ApplicationFiled: January 19, 2007Publication date: June 10, 2010Applicant: MTU Aero Engines GmbHInventor: John Sharp
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Publication number: 20100125990Abstract: A method and device for the surface peening, especially ultrasonic shot-peening, of at least one partial element of a component of a gas turbine, is disclosed. The partial element, e.g., a sealing fin, and at least one surface of a vibration device impinging the blasting material are positioned relative to each other at an angle between 70° and 90° based on the direction of extension of the sealing fin.Type: ApplicationFiled: December 5, 2007Publication date: May 27, 2010Applicant: MTU Aero Engines GmbHInventors: Erwin Bayer, Max Niegl, Holger Polanetzki, Thomas Peschke, Thomas Dautl, Philipp Thuemmler
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Patent number: 7721555Abstract: A gas turbine, especially an aircraft engine is provided. The gas turbine comprises at least one compressor (15, 16), at least one combustion chamber (17), at least one turbine (18, 19), and at least one generator (20) for generating electrical energy, each generator (20) comprising at least one stator (25) and at least one rotor (22). Each rotor (22) of each generator (20) is embodied as a free-wheeling generator turbine that is driven by a gas flow in such a way that it rotates in relation to the respective stator (25) of the respective generator (20) and thus generates electrical energy from the kinetic energy of the gas flow.Type: GrantFiled: January 29, 2005Date of Patent: May 25, 2010Assignee: MTU Aero Engines GmbHInventors: John Sharp, Andreas Kreiner
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Publication number: 20100119706Abstract: A method for producing an abradable coating for a component of a turbo-machine is disclosed. The method includes a) a powdery material is pretreated; b) a processable preliminary product is produced which is to be applied to a component that is to be coated; c) the preliminary product is applied to the component that is to be coated; d) a synthetic binder contained in the preliminary product is burned off; e) the component is sintered; and f) the component is post-processed. The method for producing an abradable coating for a turbo-machine eliminates the drawbacks of the solutions known from the prior art. In particular, the method is inexpensive, can easily be combined with other production process steps, for example, thermal treatments that have to be carried out anyway, and is also suitable as a method for repairs.Type: ApplicationFiled: April 12, 2008Publication date: May 13, 2010Applicant: MTU Aero Engines GmbHInventor: Andre Werner
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Publication number: 20100108745Abstract: A method for the repair of a component by a solder is disclosed. The method is performed under specifically selected vacuum conditions in order to prevent oxidation and vaporization.Type: ApplicationFiled: February 15, 2008Publication date: May 6, 2010Applicant: MTU Aero Engines GmbHInventors: Paul Heinz, Robert Singer
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Publication number: 20100108538Abstract: A method for stripping a component, in particular a gas turbine component, to completely or partially remove a multilayer or sandwich antiwear coating from the surface of the component, the antiwear coating including at least one relatively hard ceramic layer and at least one relatively soft metallic layer is disclosed. According to the present invention, in order to remove the multilayer or sandwich antiwear coating, the component is placed in a bath of an alkaline electrolyte, the component placed in the electrolyte being stripped at a current density of between 1 A/dm2 and 20 A/dm2.Type: ApplicationFiled: May 2, 2008Publication date: May 6, 2010Applicant: MTU Aero Engines GmbHInventors: Anton Albrecht, Wolfgang Eichmann, Georgios Paronis, Thomas Uihlein
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Patent number: 7708529Abstract: A rotor of a turbo engine, e.g., a gas turbine rotor, has a rotor base member, the rotor base member having a groove extending in the circumferential direction of the rotor base member, and having a plurality of rotor blades, each rotor blade having a blade, a blade root and a blade platform positioned between the blade and the blade root, and the rotor blades being anchored in the groove of the rotor base member by their blade roots. The groove and the blade roots have a profile, such that the blade roots of the rotor blades are insertable by a tilting motion or swiveling motion into the circumferentially extending groove of the rotor base member, and in the circumferential direction, a width of the blade root corresponds approximately to a width of the blade platform of the specific rotor blade.Type: GrantFiled: October 20, 2005Date of Patent: May 4, 2010Assignee: MTU Aero Engines GmbHInventor: Hermann Klingels
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Publication number: 20100104418Abstract: A gas turbine having a rotor which includes a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one rotor disk and a rotor cone leading from the or a rotor disk to the shaft, the downstream end of the shaft being rotatably supported in a bearing having a bearing chamber, the interior space of the shaft being designed as a flow channel for bearing-chamber sealing air, and the space surrounding the rotor cone upstream of the same being designed as a flow space for cooling air is disclosed. In the region of the rotor connection, the shaft exhibits an expanded portion, at whose upstream end, openings are provided to allow cooling air to enter, and, at whose downstream end, openings are provided to allow cooling air to exit into the space between the bearing chamber and the rotor cone, a wall separating the streams of the cooling air and of the sealing air in the shaft interior from one another.Type: ApplicationFiled: May 2, 2008Publication date: April 29, 2010Applicant: MTU Aero Engines GmbHInventors: Wilfried Weidmann, Moritz Wirth