Patents by Inventor Uwe Ruedel
Uwe Ruedel 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: 10139112Abstract: The invention relates to an annular combustion chamber of a gas turbine having a machine axis. The combustion chamber includes at least two zones. A first zone receives the fuel/air mixture of a plurality of burners. A second zone guides the hot gases being produced by the burners from the first zone to an entrance of a turbine section of said gas turbine. An annular transition liner includes a plurality of liner segments located at the transition between said first zone and second zone. Each of the liner segments includes with respect to the axial hot gas flow a leading edge, a trailing edge, and two sidewalls, and is provided with axial mounting means at the leading and trailing edges, such that the liner segment can be installed in axial direction and is axially fixed by respective segments of the neighboring first zone.Type: GrantFiled: June 2, 2015Date of Patent: November 27, 2018Assignee: General Electric CompanyInventors: Uwe Rüdel, Urs Benz, Christoph Appel, Ivan Lenuzzi
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Publication number: 20150354826Abstract: The invention relates to an annular combustion chamber of a gas turbine having a machine axis. The combustion chamber includes at least two zones. A first zone receives the fuel/air mixture of a plurality of burners. A second zone guides the hot gases being produced by the burners from the first zone to an entrance of a turbine section of said gas turbine. An annular transition liner includes a plurality of liner segments located at the transition between said first zone and second zone. Each of the liner segments includes with respect to the axial hot gas flow a leading edge, a trailing edge, and two sidewalls, and is provided with axial mounting means at the leading and trailing edges, such that the liner segment can be installed in axial direction and is axially fixed by respective segments of the neighboring first zone.Type: ApplicationFiled: June 2, 2015Publication date: December 10, 2015Inventors: Uwe RÜDEL, Urs BENZ, Christoph APPEL, Ivan LENUZZI
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Patent number: 9157637Abstract: An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimited by the burner wall, to a combustion chamber. In the mixing chamber the hot combustion gas is mixed with an injected fuel, where cooling air from the outside of the burner wall flows through effusion holes in the burner wall into an interior of the mixing chamber. The cooling air, on the outside of the burner wall, is deflected in a directed manner in its flow direction by means of deflection elements which are in a distributed arrangement.Type: GrantFiled: August 26, 2011Date of Patent: October 13, 2015Assignee: ALSTOM TECHNOLOGY LTD.Inventors: Madhavan Poyyapakkam, Adnan Eroglu, Andrea Ciani, Diane Lauffer, Uwe Ruedel
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Patent number: 9097118Abstract: A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.Type: GrantFiled: September 6, 2011Date of Patent: August 4, 2015Assignee: ALSTOM TECHNOLOGY LTD.Inventors: Martin Schnieder, Jörg Krückels, Uwe Rüdel, Christoph Appel, Urs Benz
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Patent number: 8635874Abstract: An exemplary combustor includes at least a portion having an inner liner and an outer cover plate, which together form an interposed cooling chamber. A plurality of hollow elements extend from the liner and protrude into the cooling chamber. Each hollow element defines a damping volume connected to an inner volume of the combustion chamber via a calibrated duct. During operation, the hollow elements damp pressure pulsations and, in addition, also transfer heat.Type: GrantFiled: March 20, 2012Date of Patent: January 28, 2014Assignee: Alstom Technology LtdInventors: Adnan Eroglu, Ewald Freitag, Uwe Rüdel, Urs Benz, Andreas Huber
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Patent number: 8434313Abstract: A thermal machine, especially a gas turbine, includes an annular combustor which is outwardly delimited by an outer shell and an inner shell (33) and through which a hot gas axially flows. The outer shell and inner shell (33) are each provided with a concentric cooling shroud (31) which is attached at a distance on their outer side, forming a cooling passage (32) through which cooling passage (32) cooling air flows in a direction which is opposite to the hot gas flow. The cooling of the combustor is improved by at least one of the cooling shrouds (31), on the side on which the cooling air enters the cooling passage (32), having an outwardly curved, rounded inlet edge (37) for improving the inflow conditions.Type: GrantFiled: August 13, 2009Date of Patent: May 7, 2013Assignee: ALSTOM Technology Ltd.Inventors: Remigi Tschuor, Hartmut Hähnle, Uwe Rüdel
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Publication number: 20120260657Abstract: An exemplary combustor includes at least a portion having an inner liner and an outer cover plate, which together form an interposed cooling chamber. A plurality of hollow elements extend from the liner and protrude into the cooling chamber. Each hollow element defines a damping volume connected to an inner volume of the combustion chamber via a calibrated duct. During operation, the hollow elements damp pressure pulsations and, in addition, also transfer heat.Type: ApplicationFiled: March 20, 2012Publication date: October 18, 2012Applicant: ALSTOM Technology LtdInventors: Adnan EROGLU, Ewald Freitag, Uwe Rüdel, Urs Benz, Andreas Huber
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Publication number: 20120060503Abstract: A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.Type: ApplicationFiled: September 6, 2011Publication date: March 15, 2012Applicant: ALSTOM TECHNOLOGY LTDInventors: Martin SCHNIEDER, Jörg Krückels, Uwe Rüdel, Christoph APPEL, Urs BENZ
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Publication number: 20120047908Abstract: An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimited by the burner wall, to a combustion chamber. In the mixing chamber the hot combustion gas is mixed with an injected fuel, where cooling air from the outside of the burner wall flows through effusion holes in the burner wall into an interior of the mixing chamber. The cooling air, on the outside of the burner wall, is deflected in a directed manner in its flow direction by means of deflection elements which are in a distributed arrangement.Type: ApplicationFiled: August 26, 2011Publication date: March 1, 2012Applicant: ALSTOM Technology LtdInventors: Madhavan Poyyapakkam, Adnan Eroglu, Andrea Ciani, Diane Lauffer, Uwe Ruedel
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Publication number: 20100037621Abstract: A thermal machine, especially a gas turbine, includes an annular combustor which is outwardly delimited by an outer shell and an inner shell (33) and through which a hot gas axially flows. The outer shell and inner shell (33) are each provided with a concentric cooling shroud (31) which is attached at a distance on their outer side, forming a cooling passage (32) through which cooling passage (32) cooling air flows in a direction which is opposite to the hot gas flow. The cooling of the combustor is improved by at least one of the cooling shrouds (31), on the side on which the cooling air enters the cooling passage (32), having an outwardly curved, rounded inlet edge (37) for improving the inflow conditions.Type: ApplicationFiled: August 13, 2009Publication date: February 18, 2010Inventors: Remigi Tschuor, Hartmut Hähnle, Uwe Rüdel