Patents by Inventor Thorsten Mattheis
Thorsten Mattheis 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: 11865611Abstract: A production method for a component having integrated channels for internal fluid guidance, having a first region, which is connected to a second region, and wherein the channels extend both through the first region and through the second region. The geometry of the component is modified to the technological characteristics of both production methods. The first region is produced by a method for casting using lost models without undercuts, and proceeding from the first region, the second region is built up using an additive manufacturing method.Type: GrantFiled: January 22, 2020Date of Patent: January 9, 2024Assignee: Siemens Energy Global GmbH & Co. KGInventors: Sören Fenske, Thorsten Mattheis, Martin Schäfer
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Publication number: 20220105562Abstract: A production method for a component having integrated channels for internal fluid guidance, having a first region, which is connected to a second region, and wherein the channels extend both through the first region and through the second region. The geometry of the component is modified to the technological characteristics of both production methods. The first region is produced by a method for casting using lost models without undercuts, and proceeding from the first region, the second region is built up using an additive manufacturing method.Type: ApplicationFiled: January 22, 2020Publication date: April 7, 2022Applicant: Siemens Energy Global GmbH & Co. KGInventors: Sören Fenske, Thorsten Mattheis, Martin Schäfer
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Patent number: 11224926Abstract: A method for producing a cavity in a blade platform of a blade, in particular of a turbine blade, as part of a blade-platform cooling system, wherein the method has the steps of: producing a first bore from a first platform lateral face in the direction of an opposite second platform lateral face, with a first opening in the first platform lateral face being created, and expanding the first bore in a fan-like manner by an electrical discharge machining method, in particular using a wire- or bar-form electrode, such that the first opening, created in the first step, of the first bore represents the starting point of the fan-like expansion. A blade is produced in particular with such a method.Type: GrantFiled: January 10, 2018Date of Patent: January 18, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Fathi Ahmad, Daniela Koch, Markus Lempke, Thorsten Mattheis, Axel Podschwadek, Radan Radulovic, Anne Weidenmüller
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Publication number: 20200141245Abstract: A method for producing a cavity in a blade platform of a blade, in particular of a turbine blade, as part of a blade-platform cooling system, wherein the method has the steps of: producing a first bore from a first platform lateral face in the direction of an opposite second platform lateral face, with a first opening in the first platform lateral face being created, and expanding the first bore in a fan-like manner by an electrical discharge machining method, in particular using a wire- or bar-form electrode, such that the first opening, created in the first step, of the first bore represents the starting point of the fan-like expansion. A blade is produced in particular with such a method.Type: ApplicationFiled: January 10, 2018Publication date: May 7, 2020Applicant: Siemens AktiengesellschaftInventors: Fathi Ahmad, Daniela Koch, Markus Lempke, Thorsten Mattheis, Axel Podschwadek, Radan Radulovic, Anne Weidenmüller
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Publication number: 20170314400Abstract: A hollow blade body for a hollow blade, has a blade wall which has a pressure side which has at least one first blade connection element on the inner side thereof, and a suction side which has at least one second blade connection element diametrically opposite to the first blade connection element on the inner side thereof, wherein the first blade connection element can be engaged with at least one first rib connection element which is arranged on a first longitudinal end of an insertion rib, and the second blade connection element can be engaged with at least one second rib connection element which is arranged on a second longitudinal end of the insertion rib facing away from the first longitudinal end in such a way that the insertion rib is fixed on the hollow blade body and effects a stiffening of the hollow blade.Type: ApplicationFiled: October 19, 2015Publication date: November 2, 2017Applicant: Siemens AktiengesellschaftInventors: Fathi Ahmad, Björn Buchholz, Ralph Gossilin, Daniela Koch, Thorsten Mattheis, Radan Radulovic, Marco Schüler
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Publication number: 20160319675Abstract: A rotor blade for a gas turbine has a pressure-side wall and a suction-side wall, a tip cap, a cavity which is formed by the inner surface of the pressure-side wall, the suction-side wall and the tip cap, and a squealer which extends radially from the pressure-side and suction-side walls, a half-space formed by the outer surface of the tip cap and the squealer, and a cooling channel which leads from the cavity to the outside of the squealer. The tip cap has a recess which extends from the half-space into the tip cap such that the recess divides the cooling channel into a first part that communicates with the cavity and a second part that communicates with the outside space.Type: ApplicationFiled: April 22, 2016Publication date: November 3, 2016Applicant: Siemens AktiengesellschaftInventors: Fathi Ahmad, Horst-Michael Dreher, Thorsten Mattheis, Christian Menke
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Patent number: 8257032Abstract: A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.Type: GrantFiled: January 17, 2008Date of Patent: September 4, 2012Assignee: Siemens AktiengesellschaftInventors: Alexander R. Beeck, Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Eβer, Dirk Goldschmidt, Torsten Koch, Rudolf Küperkoch, Thorsten Mattheis, Jan Münzer, Ralf Müsgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg
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Publication number: 20120118524Abstract: A core die is provided. The core die includes a first half and a second half where a cavity is formed between the two. Pins are arranged on the halves and the pins are replaceable. By virtue of the modular inner structure of a core die, the core die may be matched to the desired changes of the core, by small changes, more quickly and more easily than would be the case if the core die had only one part or if the pins were a fixed component of the core die halves.Type: ApplicationFiled: October 18, 2011Publication date: May 17, 2012Inventors: Fathi Ahmad, Winfried Esser, Giuseppe Gaio, Waldemar Heckel, Rudolf Küperkoch, Oliver Lüsebrink, Thorsten Mattheis, Mirko Milazar, Artur Mol, Uwe Paul, Oliver Ricken, Oliver Schneider
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Patent number: 8128357Abstract: The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.Type: GrantFiled: February 21, 2007Date of Patent: March 6, 2012Assignee: Siemens AktiengesellschaftInventors: Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Eβer, Dirk Goldschmidt, Torsten Koch, Rudolf Küperkoch, Thorsten Mattheis, Jan Münzer, Ralf Müsgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg
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Patent number: 8021118Abstract: A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is characterized according to the invention in that the at least one cooling medium passage emerges from the platform at at least two connecting openings, and the turbine blade has at least one supplementary component which can be fastened on the platform, with a communicating passage, which is designed for interconnecting the connecting openings in a fluid-guiding manner.Type: GrantFiled: October 16, 2007Date of Patent: September 20, 2011Assignee: Siemens AktiengesellschaftInventors: Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Eβer, Dirk Goldschmidt, Torsten Koch, Rudolf Küperkoch, Thorsten Mattheis, Jan Münzer, Ralf Müsgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg
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Publication number: 20110188999Abstract: An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.Type: ApplicationFiled: July 8, 2009Publication date: August 4, 2011Inventors: Stefan Braun, Christian Cornelius, Annika Emde, Andreas Heilos, Olaf Hein, Thomas Hofbauer, Christian Lerner, Silvio-Ulrich Martin, Thorsten Mattheis, Ralf Müsgen, Eckart Schumann, Rostislav Teteruk, Adam Zimmermann
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Patent number: 7832988Abstract: A turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements is provided. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by a high-temperature and high-pressure bonding process. In the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit.Type: GrantFiled: May 29, 2007Date of Patent: November 16, 2010Assignee: Siemens AktiengesellschaftInventors: Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Eβer, Dirk Goldschmidt, Torsten Koch, Rudolf Küperkoch, Thorsten Mattheis, Jan Münzer, Ralf Müsgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg
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Publication number: 20100014980Abstract: There is described a turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by means of a high-temperature high-pressure bonding process and, under certain circumstances, may come apart at the blade tip. In order to prevent this, in the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit.Type: ApplicationFiled: May 29, 2007Publication date: January 21, 2010Inventors: Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Esser, Dirk Goldschmidt, Torsten Koch, Rudolf Kuperkoch, Thorsten Mattheis, Jan Munzer, Ralf Musgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg
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Publication number: 20090304503Abstract: The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.Type: ApplicationFiled: February 21, 2007Publication date: December 10, 2009Inventors: Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Esser, Dirk Goldschmidt, Torsten Koch, Rudolf Küperkoch, Thorsten Mattheis, Jan Münzer, Ralf Müsgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg
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Publication number: 20080267771Abstract: A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.Type: ApplicationFiled: January 17, 2008Publication date: October 30, 2008Inventors: Alexander R. Beeck, Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Esser, Dirk Goldschmidt, Torsten Koch, Rudolf Kuperkoch, Thorsten Mattheis, Jan Munzer, Ralf Musgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg
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Publication number: 20080240927Abstract: A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is characterized according to the invention in that the at least one cooling medium passage emerges from the platform at at least two connecting openings, and the turbine blade has at least one supplementary component which can be fastened on the platform, with a communicating passage, which is designed for interconnecting the connecting openings in a fluid-guiding manner.Type: ApplicationFiled: October 16, 2007Publication date: October 2, 2008Inventors: Katharina Bergander, Georg Bostanjoglo, Tobias Buchal, Winfried Esser, Dirk Goldschmidt, Torsten Koch, Rudolf Kuperkoch, Thorsten Mattheis, Jan Munzer, Ralf Musgen, Matthias Oechsner, Ursula Pickert, Volker Vosberg