Patents by Inventor Alexander Beeck
Alexander Beeck 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: 8770924Abstract: A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.Type: GrantFiled: July 7, 2011Date of Patent: July 8, 2014Assignee: Siemens Energy, Inc.Inventors: Alexander Beeck, Malberto Gonzalez, Jerome H. Katy, David J. Wiebe
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Patent number: 8376697Abstract: A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.Type: GrantFiled: November 3, 2009Date of Patent: February 19, 2013Assignee: Siemens Energy, Inc.Inventors: David J. Wiebe, Brian J. Wessell, Todd Ebert, Alexander Beeck, George Liang, Walter H. Marussich
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Publication number: 20130011242Abstract: A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.Type: ApplicationFiled: July 7, 2011Publication date: January 10, 2013Inventors: Alexander Beeck, Malberto Gonzalez, Jerome H. Katy, David J. Wiebe
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Publication number: 20100074731Abstract: A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.Type: ApplicationFiled: November 3, 2009Publication date: March 25, 2010Inventors: David J. Wiebe, Brian J. Wessell, Todd Ebert, Alexander Beeck, George Liang, Walter H. Marussich
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Publication number: 20070020102Abstract: The invention relates to a gas turbine blade or vane ring having a supporting structure and gas turbine blades or vanes secured to it. The gas turbine blades or vanes have a blade or vane root, which is successively adjoined by a platform and then a blade profile which is curved in the longitudinal direction, the blade or vane root running in the longitudinal direction of the blade profile, and the platform having two platform longitudinal edges which are bent parallel and run in the longitudinal direction. To provide an alternative gas turbine blade or vane ring with simplified assembly, it is proposed that the blade or vane root be shaped in such a manner that the suction-side or pressure-side blade or vane root surface of the associated platform longitudinal edge be curved convexly or concavely, respectively. Moreover, the invention relates to the use of a gas turbine blade or vane ring of this type.Type: ApplicationFiled: August 29, 2005Publication date: January 25, 2007Inventors: Alexander Beeck, Stefan Irmisch
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Publication number: 20070020100Abstract: The invention relates to a turbine blade or vane for a gas turbine, having a blade or vane root, which is successively adjoined by a platform region with a transversely running platform and then a blade or vane profile which is curved in the longitudinal direction, having a platform surface, which is provided at the platform and can be exposed to hot gas, and having at least one cavity, which is open on the root side, through which a coolant can flow and which extends through the blade or vane root and at least into the platform region and is surrounded by an inner wall, the contour of which, running in the platform region, is set back with respect to the contour running in the blade or vane root, so as to form a recess.Type: ApplicationFiled: August 29, 2005Publication date: January 25, 2007Inventors: Alexander Beeck, Stefan Irmisch
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Publication number: 20060198916Abstract: A process for forming a ceramic object using selective laser sintering of ceramic powder is provided. The chemical composition and size distribution of the powder may be varied between various regions of the object, and the temperature achieved by laser heating may be varied between regions to achieve the desired degree of densification. In one embodiment, a ceramic mold (1) is formed in to have an envelope portion (4) and a core portion (7) with differing properties using a fast prototyping laser sintering process.Type: ApplicationFiled: April 1, 2004Publication date: September 7, 2006Inventors: Alexander Beeck, Boris Bublath, Nikolai-Alexander Daus, Dirk Goldschmidt
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Patent number: 6916021Abstract: The present invention relates to a sealing arrangement which is formed between a rotating assembly (4, 6) and a static assembly (3, 14, 15). In this sealing arrangement, the rotating assembly (4, 6, 16) has at least one cutting element (1) which engages in a counterpart surface on the static component. The present sealing arrangement is distinguished by the fact that the cutting element (1) is designed as a chipping device with a geometrically determined cutting edge with respect to the counterpart surface (2) or forms a chipping device of this type when the rotating assembly is rotating. The proposed sealing arrangement reduces the wear to the cutting element even in the event of adverse rotation or temperature conditions.Type: GrantFiled: March 10, 2003Date of Patent: July 12, 2005Assignee: Alstom Technology Ltd.Inventors: Alexander Beeck, Bruno Benedetti, Andreas Kieninger, Ulrich Rathmann
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Patent number: 6857639Abstract: The invention relates to a gap seal (6) for sealing a gap (3) between two adjacent components (1, 2), in particular of turbo machines, with the following characteristics: each component (1) has one each groove (7) that is open towards the gap (3), the two grooves (7) are essentially facing each other in the gap (3), in each groove (7), a compensation body (16) is movably positioned transversely to the longitudinal groove direction and parallel to the gap plane (10), each compensation body (11) abuts the groove bottom (9) of the corresponding groove (7) in a sealing manner, each compensation body (11) has a V-shaped receiving groove (14) that is open towards the facing compensation body (11), a mutual sealing body (16) has a rhombus-shaped cross-section and projects with outer sides (17) into both receiving grooves (14), the straight inner sides (15) of each receiving groove (14) are angled towards each other at the same angle as the straight outer sides (17), in each receiving groove (14), at least one outType: GrantFiled: July 3, 2003Date of Patent: February 22, 2005Assignee: ALSTOM Technology LTDInventors: Alexander Beeck, Arkadi Fokine, Edouard Sloutski, Sergey Vorontsov
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Patent number: 6739594Abstract: A sealing arrangement between two radially adjoining components of an assembly that rotates during operation, in particular between the rotor and the rotating blade of a gas turbine component includes a sealing element in a depression of an inner one of the two components at the boundary surface to the outer one of the two components. The sealing element is designed in such a way that it does not or does only slightly project beyond the depression during assembly and that, during rotation of the assembly, the centrifugal force acting on it produces a sealing joint between the components. The present sealing arrangement permits an easy installation of rotating blades to the rotor of a gas turbine.Type: GrantFiled: November 19, 2001Date of Patent: May 25, 2004Assignee: Alstom Technology LTDInventors: Alexander Beeck, Ulrich Rathmann
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Process for the rapid production of hollow components of flow machines for manufacturing development
Patent number: 6705383Abstract: A process for the rapid production of hollow components of flow machines, in particular turbine blades, for manufacturing development. In the process, the turbine blade to be produced is divided into two or more portions such that none of the portions has a cavity. The two or more portions are individually cast by means of a Rapid Prototype process, and are then joined together to form the hollow component. The process makes possible the simple and cost-effective production of turbine blades for manufacturing development, in particular for the development of the cooling systems.Type: GrantFiled: December 5, 2001Date of Patent: March 16, 2004Assignee: Alstom Technology LtdInventors: Alexander Beeck, John Fernihough -
Publication number: 20040041351Abstract: The invention relates to a gap seal (6)for sealing a gap (3) between two adjacent components (1,2), in particular in turbo machines. A sealing body (7) has a band (18) with a cross-section that is bent in such a way that two contact zones (8) formed on it abut with a preloan against two facing sealing surfaces (9) of components (1,2). The contact zones (8) are able to deflect resiliently when the distance between the sealing surfaces (9) is reduced. A support zone (11) formed between the contact zones (8) is supported on a step (10) vertically to the spring movement. The step (10) is formed on one of the components (2) and projects from its sealing surface (9) towards the sealing surface (9) of the other component (1).Type: ApplicationFiled: July 3, 2003Publication date: March 4, 2004Inventors: Alexander Beeck, Arkadi Fokine, Igor Ossipov, Edouard Sloutski
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Publication number: 20040041350Abstract: The invention relates to a gap seal (6) for sealing a gap (3) between two adjacent components (1, 2), in particular of turbo machines, with the following characteristics:Type: ApplicationFiled: July 3, 2003Publication date: March 4, 2004Inventors: Alexander Beeck, Arkadi Fokine, Edouard Sloutski, Sergey Vorontsov
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Patent number: 6695036Abstract: The invention relates to a method for producing a cast part of a thermal turbo-machine by way of a known casting process. Between a model mold and a ceramic insert, projections are located on the ceramic insert, whereby the projections have an angle (&agr;, &bgr;) between the center line and the outer edge of the projections of less than 30°, and whereby the projections are used both for the fixation of the insert during the casting process and for the reduction of the notch factor inside the recesses created in the cast part.Type: GrantFiled: November 26, 2001Date of Patent: February 24, 2004Assignee: Alstom (Switzerland) LtdInventors: Herbert Brandl, Alexander Hoffs, Roland Muecke, Sergej Riazantsev, Alexander Beeck
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Patent number: 6682304Abstract: A cooled gas turbine blade with a shroud in which a cooling channel system is provided, which is closed off radially to the gas turbine blade with a cover plate is characterized in that the cover plate has a circumferential edge, along the entire extension of which the cover plate enters into a continuous shape-mated connection or a plurality of locally limited shape-mated connections with the shroud.Type: GrantFiled: November 30, 2001Date of Patent: January 27, 2004Assignee: Alstom Technology LtdInventors: Alexander Beeck, Reinhard Fried, Markus Oehl
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Publication number: 20040012151Abstract: The present invention relates to a sealing arrangement which is formed between a rotating assembly (4, 6) and a static assembly (3, 14, 15). In this sealing arrangement, the rotating assembly (4, 6, 16) has at least one cutting element (1) which engages in a counterpart surface on the static component. The present sealing arrangement is distinguished by the fact that the cutting element (1) is designed as a chipping device with a geometrically determined cutting edge with respect to the counterpart surface (2) or forms a chipping device of this type when the rotating assembly is rotating. The proposed sealing arrangement reduces the wear to the cutting element even in the event of adverse rotation or temperature conditions.Type: ApplicationFiled: March 10, 2003Publication date: January 22, 2004Inventors: Alexander Beeck, Bruno Benedetti, Andreas Kieninger, Ulrich Rathmann
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Patent number: 6644920Abstract: A method of forming a curved cooling channel into a gas turbine component such as a turbine blade uses an electrode in the form of a helix. The electrode is driven to rotate around the central rotational axis of the helix and axially along the central rotational axis. A turbine blade for a gas turbine component is provided with at least one helical cooling channel.Type: GrantFiled: November 26, 2001Date of Patent: November 11, 2003Assignee: Alstom (Switzerland) LtdInventors: Alexander Beeck, Bernhard Weigand
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Patent number: 6640597Abstract: A method is disclosed for reducing the variance in the coolant consumption of components of a turbo-machine, in particular a gas turbine. The components are provided with one or more holes for the passage of a coolant, wherein a surface roughness existing inside the holes is reduced by mechanical finishing. The method is characterized by mechanical finishing that is performed by reshaping rough points that cause the surface roughness using a cold working process such as at least one of beating, pressing and rolling. The method permits a simple reduction of the surface roughness without creating finishing residues that could result in obstructions of the holes.Type: GrantFiled: December 6, 2001Date of Patent: November 4, 2003Assignee: ALSTOM (Switzerland) LtdInventors: Alexander Beeck, Christoph Nagler, Mark Richter
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Patent number: 6641360Abstract: Described is a device and a method for cooling a platform of a turbine blade comprising a blade root, a vane with a leading and trailing edge, as well as a blade tip with a platform, through which platform extends radially, at least in part, at least one cooling channel that is connected with at least one outlet channel exiting via an outlet opening at the platform. The invention is characterized in that the outlet channel has, adjacent to the outlet opening, a longitudinal channel direction that extends, in projection, longitudinally to the turbine blade in an essentially co-parallel manner with respect to the flow direction of a local flow field of a mass flux relatively passing by the turbine blade, said flow field directly flowing over the exit opening.Type: GrantFiled: December 6, 2001Date of Patent: November 4, 2003Assignee: Alstom (Switzerland) LtdInventors: Alexander Beeck, Stefan Florjancic
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Patent number: 6589011Abstract: Described is a cooling device for a shroud of a gas turbine blade, having a cooling channel system provided in the shroud, which is provided radially to the gas turbine blade with cooling channels that are open on one side, and which is closed off with a cover plate. The invention is characterized in that, between the cover plate and the cooling channels that are open on one side, an impact cooling plate is provided in such a way that the impact cooling plate rests on the cooling channels that are open on one side, is pressed against them by force, and encloses a space with the cover plate.Type: GrantFiled: November 30, 2001Date of Patent: July 8, 2003Assignee: Alstom (Switzerland) LtdInventors: Alexander Beeck, Reinhard Fried, Markus Oehl