Patents by Inventor Siegfried Sikorski
Siegfried Sikorski has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11162367Abstract: A rotor blade airfoil (25) for a turbomachine (1) that is adapted for rotation about a longitudinal axis (2) of the turbomachine (1) is provided. The rotor blade airfoil (25) is built from an airfoil material reinforced with a fibrous material (30). At least a portion of the fibers of the fibrous material (30), in particular at least 20%, preferably at least 30% of the fibers, are oriented in a first fiber direction (31), and the first fiber direction (31) is tilted with respect to the stacking axis of the rotor blade airfoil (25).Type: GrantFiled: December 16, 2019Date of Patent: November 2, 2021Assignee: MTU Aero Engines AGInventors: Benedikt Albert, Siegfried Sikorski
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Patent number: 10830068Abstract: In a method for the generative production of a component (3), in particular of a turbo-engine component, wherein material (4) is bonded layer-by-layer selectively to a layer disposed therebeneath or to a substrate (6), according to the invention a laser (1A; 1B; 2) additionally acts on the material (4) before, during and/or after the bonding.Type: GrantFiled: October 13, 2012Date of Patent: November 10, 2020Assignee: MTU AERO ENGINES AGInventors: Wilhelm Satzger, Siegfried Sikorski, Thomas Hess, Karl-Heinz Dusel, Hans-Christian Melzer
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Publication number: 20200200015Abstract: A rotor blade airfoil (25) for a turbomachine (1) that is adapted for rotation about a longitudinal axis (2) of the turbomachine (1) is provided. The rotor blade airfoil (25) is built from an airfoil material reinforced with a fibrous material (30). At least a portion of the fibers of the fibrous material (30), in particular at least 20%, preferably at least 30% of the fibers, are oriented in a first fiber direction (31), and the first fiber direction (31) is tilted with respect to the stacking axis of the rotor blade airfoil (25).Type: ApplicationFiled: December 16, 2019Publication date: June 25, 2020Applicant: MTU Aero Engines AGInventors: Benedikt ALBERT, Siegfried SIKORSKI
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Patent number: 10633975Abstract: The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit.Type: GrantFiled: September 12, 2011Date of Patent: April 28, 2020Assignee: MTU AERO ENGINES AGInventors: Thomas Hess, Erwin Bayer, Markus Waltemathe, Klaus Broichhausen, Wilhelm Satzger, Siegfried Sikorski, Karl-Heinz Dusel, Hans-Christian Melzer
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Patent number: 10544697Abstract: The present invention relates to a process for producing a seal arrangement (1) for a turbomachine which comprises a seal support (2) and a stripping lining (3) which is arranged on the seal support, wherein the seal support comprises a fiber-reinforced plastic and the stripping lining comprises polysiloxane, and wherein the seal support and the stripping lining are prepared in a non-cured state and are arranged in direct contact with one another in accordance with the configuration of the seal arrangement, and are subsequently subjected to a common curing process such that fiber-reinforced plastic and polysiloxane cross-link with one another. The present invention further relates to a correspondingly produced seal arrangement and to a turbomachine having such a seal arrangement.Type: GrantFiled: September 19, 2014Date of Patent: January 28, 2020Assignee: MTU AERO ENGINES AGInventors: Siegfried Schmid, Michael Schober, Siegfried Sikorski, Axel Mattschas, Robert Bader
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Patent number: 9952236Abstract: Disclosed is a method for monitoring a generative fabrication process in which a component is formed in an installation space from a multiplicity of layers by using a three-dimensional data model and a following layer is fixed to a preceding layer by means of a high-energy beam. The method comprises detecting the component at least optically and detecting the installation space thermally during layer application. Also disclosed is a device for carrying out the method.Type: GrantFiled: January 11, 2012Date of Patent: April 24, 2018Assignee: MTU AERO ENGINES AGInventors: Wilhelm Satzger, Siegfried Sikorski, Karl-Heinz Dusel, Wilhelm Meir, Bertram Kopperger, Josef Waermann, Andreas Jakimov, Manuel Hertter, Hans-Christian Melzer, Thomas Hess
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Publication number: 20150078893Abstract: The present invention relates to a process for producing a seal arrangement (1) for a turbomachine which comprises a seal support (2) and a stripping lining (3) which is arranged on the seal support, wherein the seal support comprises a fiber-reinforced plastic and the stripping lining comprises polysiloxane, and wherein the seal support and the stripping lining are prepared in a non-cured state and are arranged in direct contact with one another in accordance with the configuration of the seal arrangement, and are subsequently subjected to a common curing process such that fiber-reinforced plastic and polysiloxane cross-link with one another. The present invention further relates to a correspondingly produced seal arrangement and to a turbomachine having such a seal arrangement.Type: ApplicationFiled: September 19, 2014Publication date: March 19, 2015Inventors: Siegfried SCHMID, Michael SCHOBER, Siegfried SIKORSKI, Axel MATTSCHAS, Robert BADER
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Publication number: 20140334924Abstract: In a method for the generative production of a component (3), in particular of a turbo-engine component, wherein material (4) is bonded layer-by-layer selectively to a layer disposed therebeneath or to a substrate (6), according to the invention a laser (1A; 1B; 2) additionally acts on the material (4) before, during and/or after the bonding.Type: ApplicationFiled: October 13, 2012Publication date: November 13, 2014Applicant: MTU AERO ENGINES AGInventors: Wilhelm Satzger, Siegfried Sikorski, Thomas Hess, Karl-Heinz Dusel, Hans-Christian Melzer
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Publication number: 20140065343Abstract: The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit.Type: ApplicationFiled: September 12, 2011Publication date: March 6, 2014Applicant: MTU AERO ENGINES AGInventors: Thomas Hess, Erwin Bayer, Markus Waltemathe, Klaus Broichhausen, Wilhelm Satzger, Siegfried Sikorski, Karl-Heinz Dusel, Hans-Christian Melzer
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Publication number: 20130343947Abstract: Disclosed is a method for monitoring a generative production process in real time, wherein a component is at least optically detected and the installation space is thermally detected when applying a layer, as well as a device for carrying out said method.Type: ApplicationFiled: January 11, 2012Publication date: December 26, 2013Applicant: MTU Aero Engines AGInventors: Wilhelm Satzger, Siegfried Sikorski, Karl-Heinz Dusel, Wilhelm Meir, Bertram Kopperger, Josef Waermann, Andreas Jakimov, Manuel Hertter, Hans-Christian Melzer, Thomas Hess
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Publication number: 20130294891Abstract: The invention provides a method for the generative manufacture of a component (1) with integrated damping for a turbomachine, in particular a gas turbine, having the following method steps: building up the component (1) in a generative manner, and introducing a damping material (2) into the component (1) during the method step of the generative building up of the component (1). The invention further provides a component (1) with integrated damping for a turbomachine, in particular a gas turbine, wherein the component (1) is built up in a generative manner, and the component (1) has a damping material (2) which is introduced into the component (1) during the generative building up of the component (1). The invention further provides a turbomachine, in particular a gas turbine, comprising such a component (1).Type: ApplicationFiled: January 10, 2012Publication date: November 7, 2013Inventors: Stefan Neuhaeusler, Wilhelm Satzger, Siegfried Sikorski, Karl-Heinz Dusel, Hans-Christian Melzer, Erwin Bayer
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Publication number: 20100074740Abstract: The invention relates to a vane ring of a turbo engine, particularly a gas turbine, comprising a vane support ring and several guide vanes that are mounted on the vane support ring. According to the invention, the vane support ring and the guide vanes are made of different materials, the materials of which the guide vanes are made being of a higher quality than the material of which the vane support ring is made.Type: ApplicationFiled: December 1, 2007Publication date: March 25, 2010Applicant: MTU AERO ENGINES, GMBHInventors: Siegfried Sikorski, Max Kraus, Karl Hoffmann, Alois Niedersüss
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Publication number: 20090041607Abstract: A method is provided for producing a sealing segment for use in compressor and turbine components, by powder injection molding, the method comprising the following steps: a) preparing a first homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binding agent; b) producing a first molded article by injection molding the first mixture; c) preparing a second homogeneous mixture of a metal powder or a mixture of metal powders or a ceramic powder or a mixture of ceramic powders and at least one binding agent, the second mixture being selected to exhibit a lower abrasion resistance than the first mixture following a subsequent joint sintering process; d) producing a second molded article as a rub strip by injection molding the second mixture; and e) joining the first and second molded articles to produce the sealing segment.Type: ApplicationFiled: February 27, 2007Publication date: February 12, 2009Applicant: MTU Aero Engines GmbHInventors: Reinhold Meier, Claus Mueller, Franz Prieschl, Siegfried Sikorski
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Publication number: 20070248780Abstract: A fiber laminate is provided, as well as a method for producing the fiber laminate and a method for making a component from the fiber laminate. The fiber laminate includes several fiber layers having reinforcement fibers extending in a preferential direction, and/or several multiaxial nonwoven fabrics consisting of reinforcement fibers, of various contours, wherein the fiber layers are fixed one under the other and/or placed in the multiaxial nonwoven one on top of the other along at least one area before contouring.Type: ApplicationFiled: July 22, 2004Publication date: October 25, 2007Applicant: MTU Aero Engines GmbhInventors: Michael Schober, Reinhold Schoenacher, Siegfried Sikorski
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Patent number: 6521331Abstract: A composite laminate or layer structure includes a substrate (2) and a cover layer (4) bonded thereon. The substrate is made up of at least one layer (3) of fiber-reinforced synthetic material. The cover layer includes at least one layer (5) of metal fibers and/or threads (6), and a metal sheet (7) forming the outer surface skin (8) of the layer structure. The metal sheet is bonded by soldering or sintering onto the metal fibers and/or threads (6), while the layer of metal fibers and/or threads in turn is bonded to the underlying fiber-reinforced synthetic material (3) by being mutually and integrally permeated by a synthetic resin matrix and bonding material. Also, the metal fibers and/or threads (6) may be intermeshed with the fibers of the synthetic material (3).Type: GrantFiled: March 2, 2000Date of Patent: February 18, 2003Assignee: MTU Aero Engines GmbHInventors: Siegfried Sikorski, Reinhold Schoenacher, Michael Schober
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Patent number: 6471485Abstract: A rotor for a propulsion plant has hybrid rotor blades arranged circumferentially around and extending essentially radially from a rotor. To reduce vibrations, the rotor blade has a metallic blade root and each blade has a metallic blade section that forms at least a portion of the blade leading edge and the area of the blade surface adjacent to the blade leading edge, and a blade section made of fiber-reinforced synthetic material or composite material. The blade sections (3, 4) of each blade (1) are so correlated to each other that damage or loss of the composite material blade section (4) still enables the propulsion plant to deliver a required emergency power.Type: GrantFiled: July 17, 2000Date of Patent: October 29, 2002Assignee: MTU Aero Engines GmbHInventors: Axel Rossmann, Siegfried Sikorski, Wolfgang Krueger
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Patent number: 6221795Abstract: The invention relates to a composite material having a substrate, which contains at least one fiber layer, and a cover layer, which adjoins the substrate and which, at least adjacent to the at least one fiber layer, contains metallic fibers and/or threads. The at least one fiber layer of the substrate and the metallic fibers and/or threads of the cover layer being saturated with binder and, as a result, the substrate and the cover layer are formed together or connected. Metallic, ceramic or glass-type particles are embedded in the cover layer in the area of the metallic fibers and/or threads. Preferably, the particles may be one or more or a combination of TiC, TiN, TiAl, Fe, steel, Ni, Si, metal alloys, diamond, or glass. In addition, the invention provides a process for manufacturing a composite material and articles of manufacture comprising the composite material, especially for rotor blades or propellers.Type: GrantFiled: October 20, 1997Date of Patent: April 24, 2001Assignee: MTU Motoren-und Turbinen-Union Muenchen GmbHInventors: Siegfried Sikorski, Michael Schober, Reinhold Schönacher
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Patent number: 5951254Abstract: A blade for a fluid flow machine such as a jet turbine engine includes a blade body (2) that is to be exposed to the fluid flow and therefore is subject to damage by erosion due to abrasive particle entrained in the fluid flow and due to thermal loading. The blade body (2) is a layered body including base layers (6) of a fiber reinforced synthetic material and a metallic cover layer (7) applied as an erosion protective layer onto at least a portion or the entirety of the surface of the base layers (6). The cover layer (7) includes metallic fibers or threads (9A, 9B) which are bonded with the fiber reinforced synthetic material of the adjacent base layers (6) by the same synthetic resin binder material permeating through and forming a matrix for all the layers (6 and 7). The metallic fibers or threads (9A, 9B) embedded in a synthetic resin matrix are characterized by a high degree of erosion resistance and a good tolerance for defects in the case of local impact or erosion damage.Type: GrantFiled: July 9, 1997Date of Patent: September 14, 1999Assignee: MTU Motoren- und Turbinen- Union Muenchen GmbHInventors: Siegfried Sikorski, Michael Schober, Reinhold Schoenacher
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Patent number: 5700743Abstract: A structural component which consists of a fiber-reinforced, composite material is provided with a protective coating against erosion. The protective coating includes an adhesion-promoting, intermediate layer on the component, an electrically insulating baked, inorganic lacquer layer for protection against erosion and an electrically conducting covering layer, for protection against lightning strikes. The covering layer consists of a baked and compressed inorganic lacquer and the lacquer of the lacquer layer and of the covering layer is baked on the component below the temperature which causes damage to the structural component or below the softening or decomposition temperature of the component. The protective layer is advantageously used for the external components of propulsion units, such as housings, nose cones or fan blades.Type: GrantFiled: March 10, 1997Date of Patent: December 23, 1997Assignee: MTU Motoren-Und Turbinen-Union Munchen GmbHInventors: Franz Puchinger, Axel Rossman, Siegfried Sikorski, Gerhard Wydra
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Patent number: 5429477Abstract: A vibration damper for rotor housings includes a rubber-elastic damping band (6) that encircles the outer circumference of the rotor housing (4) in a contour fitting manner. A clamping band (7) encircles the damping band (6) and secures the damping band to the housing (4). The clamping band is made of a material having a different modulus of elasticity than the material of the rotor housing, which achieves a detuning of the vibrational system including the rotor housing and the vibration damper as components. Such a detuning reduces the vibrational tendency of the rotor housing. Frictional rubbing between the damping band and the housing surface, and between the damping band and the clamping band effectively damps or dissipates the energy of any vibration that does occur.Type: GrantFiled: August 24, 1994Date of Patent: July 4, 1995Assignee: MTU Motoren- und Turbinen- Union Munich GmbHInventors: Siegfried Sikorski, Reinhold Schoenacher, Michael Schober, Wolfgang Diepolder