Patents by Inventor Armin Busekros
Armin Busekros 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: 10415395Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.Type: GrantFiled: May 13, 2016Date of Patent: September 17, 2019Assignee: Ansaldo Energia Switzerland AGInventors: Oliver Joseph Taheny, Sven Olmes, Armin Busekros, Carlos Simon-Delgado, Daniel Jemora, Christophe Simonet, Luca Alberti, Eugenio Rossi
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Publication number: 20160333700Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.Type: ApplicationFiled: May 13, 2016Publication date: November 17, 2016Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Oliver Joseph TAHENY, Sven OLMES, Armin BUSEKROS, Carlos SIMON-DELGADO, Daniel JEMORA, Christophe SIMONET, Luca ALBERTI, Eugenio ROSSI
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Publication number: 20160177833Abstract: Disclosed is an engine, the engine having a compressor, an expansion machine, and a shaft, the shaft having a direction of rotation. The engine includes a compressed fluid main flow path, a flow divider arranged at and fluidly connected to the compressed fluid main flow path, and a duct fluidly connecting the flow divider and components of the expansion machine. The duct is arranged such that, when the engine is operated, a fluid is guided through the duct from the flow divider towards the expansion machine components. A flow deflector device is arranged within a flow path and configured to deflect and thereby accelerate a flow therethrough directed form the flow divider towards the expansion machine components in a tangential direction, wherein the deflection can be effected into the shaft direction of rotation.Type: ApplicationFiled: December 22, 2015Publication date: June 23, 2016Applicant: General Electric Technology GmbHInventors: Carlos SIMON-DELGADO, Oliver Joseph TAHENY, Sven OLMES, Armin BUSEKROS, Luca ALBERTI, Daniel JEMORA, Eugenio ROSSI, Christophe SIMONET
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Patent number: 9181875Abstract: An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine.Type: GrantFiled: March 29, 2012Date of Patent: November 10, 2015Assignee: ALSTOM TECHNOLOGY LTDInventors: Armin Busekros, Thomas Kramer, Jochem Fischer, Juergen Hoffmann
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Publication number: 20150010389Abstract: The invention relates to a pressure casing, which includes a plurality of casing shells which are connected in a pressure-tight manner in a parting plane by means of a flange. The casing shells are pressed together with sealing effect in the parting plane in the region of the flange by means of at least one threaded bolt which extends in a through hole through the flange perpendicularly to the parting plane. Reduced temperature differences between the flange and the connecting bolts of the flanged joint are achieved by the at least one threaded bolt being charged with a heat transfer medium over a part of its length. The heat transfer medium is supplied via holes extending through the flange.Type: ApplicationFiled: June 27, 2014Publication date: January 8, 2015Inventors: Armin BUSEKROS, Robert PRZYBYL, Gregory JEUNET-MANCY
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Patent number: 8292252Abstract: In a support for a turbine, which turbine has an outer casing which is split into an upper section (11) and a lower section (12) in a horizontal parting plane, in which upper section (11) and lower section (12) are screwed to each other on a horizontal flange (13; 13a, 13b) which lies in the parting plane, the support includes a multiplicity of essentially vertical supports (31) which by an upper end act on the outer casing (18) and by the lower end are supported on a foundation. With such a support, optimum points of application on the outer casing are achieved with the threaded flange connection without limitations by one or more of the supports (31) acting by the upper end on the horizontal flange (13; 13a, 13b) and being part of the horizontal threaded flange connection.Type: GrantFiled: March 9, 2010Date of Patent: October 23, 2012Assignee: ALSTOM Technology Ltd.Inventors: Armin Busekros, Pascal Prehm, Miroslav Cindric, Dominic Bürgi
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Publication number: 20120247109Abstract: An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine.Type: ApplicationFiled: March 29, 2012Publication date: October 4, 2012Applicant: ALSTOM TECHNOLOGY LTDInventors: Armin Busekros, Thomas Kramer, Jochem Fischer, Juergen Hoffmann
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Patent number: 8028967Abstract: A device and a method for mounting a turbine engine, e.g., a gas turbine system, are described, in which a rotor unit is mounted to rotate inside a stationary external housing, having at least two supports for taking up the weight of the turbine engine, these supports being arranged at a spacing from one another in an axial longitudinal direction in relation to the external housing and at one side being articulated directly or indirectly on the external housing and at the other being supported directly or indirectly on a base frame. At least one support provides at least one support face which is supported exclusively in partial regions on at least two support plate elements. The at least one support face of the support is in operational engagement with the base frame by way of the support plate elements.Type: GrantFiled: September 16, 2008Date of Patent: October 4, 2011Assignee: Alstom Technology LtdInventors: Armin Busekros, Olatunde Omisore, Thomas Wilhelm
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Publication number: 20100237221Abstract: In a support for a turbine, which turbine has an outer casing which is split into an upper section (11) and a lower section (12) in a horizontal parting plane, in which upper section (11) and lower section (12) are screwed to each other on a horizontal flange (13; 13a, 13b) which lies in the parting plane, the support includes a multiplicity of essentially vertical supports (31) which by an upper end act on the outer casing (18) and by the lower end are supported on a foundation. With such a support, optimum points of application on the outer casing are achieved with the threaded flange connection without limitations by one or more of the supports (31) acting by the upper end on the horizontal flange (13; 13a, 13b) and being part of the horizontal threaded flange connection.Type: ApplicationFiled: March 9, 2010Publication date: September 23, 2010Inventors: Armin Busekros, Pascal Prehm, Miroslav Cindric, Dominic BÜRGI
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Patent number: 7766610Abstract: Annular or ring-segment-shaped cavities (2, 7) which are formed in particular in multi-shell (11; 12, 13) casings of turbomachines are preferably provided with suitable means for compensating for forming temperature stratifications. According to the invention, an overflow passage (14) connects two points of the cavity to one another which are situated in different circumferential positions. Arranged in the overflow passage (14) is an ejector (17) which can be operated with a motive fluid and which serves to drive a flow through the overflow passage from an upstream end (15) to a downstream end (16).Type: GrantFiled: October 7, 2005Date of Patent: August 3, 2010Assignee: Alstom Technology LtdInventors: Armin Busekros, Darran Norman, Matthias Rothbrust
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Publication number: 20090064685Abstract: A device and a method for mounting a turbine engine, e.g., a gas turbine system, are described, in which a rotor unit is mounted to rotate inside a stationary external housing, having at least two supports for taking up the weight of the turbine engine, these supports being arranged at a spacing from one another in an axial longitudinal direction in relation to the external housing and at one side being articulated directly or indirectly on the external housing and at the other being supported directly or indirectly on a base frame. At least one support provides at least one support face which is supported exclusively in partial regions on at least two support plate elements. The at least one support face of the support is in operational engagement with the base frame by way of the support plate elements.Type: ApplicationFiled: September 16, 2008Publication date: March 12, 2009Applicant: ALSTOM Technology LtdInventors: Armin BUSEKROS, Olatunde OMISORE, Thomas WILHELM
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Publication number: 20060073010Abstract: Annular or ring-segment-shaped cavities (2, 7) which are formed in particular in multi-shell (11; 12, 13) casings of turbomachines are preferably provided with suitable means for compensating for forming temperature stratifications. According to the invention, an overflow passage (14) connects two points of the cavity to one another which are situated in different circumferential positions. Arranged in the overflow passage (14) is an ejector (17) which can be operated with a motive fluid and which serves to drive a flow through the overflow passage from an upstream end (15) to a downstream end (16).Type: ApplicationFiled: October 7, 2005Publication date: April 6, 2006Applicant: ALSTOM Technology LtdInventors: Armin Busekros, Darran Norman, Matthias Rothbrust
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Patent number: 6672831Abstract: A device for setting the gap dimension for a turbomachine, in particular a gas turbine, with heat accumulation segments which are arranged on the guide-vane carrier of the rotor arrangement. At least one drive device projects radially through the turbine casing and the guide-vane carrier and is operatively connected kinematically to at least one heat accumulation segment and which, when actuated, causes a radial spacing of the heat accumulation segment. The heat accumulation segment has, in the flow direction of the turbomachine, a conical contour facing the rotor arrangement and is arranged so as to be displaceable parallel to the flow direction, and in that the drive device is connected to the heat accumulation segment directly or via an eccentric unit, in such a way that, when the drive device is actuated, the heat accumulation segment is displaced, with the result that a radial spacing between the heat accumulation segment and the moving-blade tips can be set.Type: GrantFiled: November 29, 2001Date of Patent: January 6, 2004Assignee: Alstom Technology LtdInventors: Herbert Brandl, Armin Busekros, Peter Marx, Ulrich Rathmann, Ulrich Wellenkamp
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Publication number: 20020071763Abstract: What is described is a device for setting the gap dimension for a turbomachine, in particular a gas turbine, with a multiplicity of moving blades arranged in at least one moving-blade row of a rotor arrangement, with a guide-vane carrier surrounding the rotor arrangement and a turbine casing surrounding the guide-vane carrier, with a multiplicity of heat accumulation segments which are arranged on the guide-vane carrier of the rotor arrangement and at least opposite the moving-blade tips and which, together with the moving-blade tips, enclose a gap, and with at least one drive means which projects radially through the turbine casing and the guide-vane carrier and is operatively connected kinematically to at least one heat accumulation segment and which, when actuated, causes a radial spacing of the heat accumulation segment.Type: ApplicationFiled: November 29, 2001Publication date: June 13, 2002Inventors: Herbert Brandl, Armin Busekros, Peter Marx, Ulrich Rathmann, Ulrich Wellenkamp