Patents by Inventor Torsten Wind
Torsten Wind 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: 11313559Abstract: The invention refers to a method and a device for flame stabilization in a burner system of a stationary combustion engine, preferably a stationary gas turbine, in which a flow of an air/fuel mixture is produced and being swirled to form a vortex flow to which a swirl number is assignable before entering a combustion zone in which the vortex flow of the air/fuel mixture is ignited to form a flame within a reverse flow zone caused by vortex breakdown. The swirl number perturbation driven by thermoacoustic oscillation inside the burner system is controlled by affecting the vortex flow actively before entering the combustion zone on basis of changing a flame transfer function assigned to the burner system with the proviso of minimizing pulsation amplitudes of the flame transfer function.Type: GrantFiled: February 22, 2016Date of Patent: April 26, 2022Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Fernando Biagioli, Alessandro Scarpato, Torsten Wind, Khawar Syed
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Patent number: 11174784Abstract: An exemplary gas turbine power plant includes a gas turbine with a compressor having a compressor inlet. A combustion chamber follows the compressor and a turbine follows the combustion chamber. A cross section of the compressor inlet includes an inner sector and an outer sector in relation to the axis of rotation of the compressor. A plurality of feed ducts introduces oxygen-reduced gas into the inner sector of the compressor inlet. The plurality of feed ducts is arranged in the compressor inlet so as to be distributed in a circumferential direction on a circle concentrically with respect to the axis of the gas turbine.Type: GrantFiled: December 29, 2017Date of Patent: November 16, 2021Assignee: ANSALDO ENERGIA SWITZEERLAND AGInventors: Jaan Hellat, Eribert Benz, Frank Graf, Torsten Wind, Felix Guethe, Klaus Doebbeling
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Gas turbine combustor with heat exchanger between rich combustion zone and secondary combustion zone
Patent number: 11041623Abstract: A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.Type: GrantFiled: May 14, 2018Date of Patent: June 22, 2021Assignee: General Electric CompanyInventors: Felipe Bolanos, Torsten Wind, Fernando Biagioli -
Patent number: 10544736Abstract: A combustion chamber including a body with a fuel supply duct for supplying a fuel into the body and a carrier air supply duct for supplying air into the body. An adjusting system adjusts the carrier air mass flow supplied into the body according to the features of the fuel.Type: GrantFiled: April 4, 2014Date of Patent: January 28, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Madhavan Narasimhan Poyyapakkam, Khawar Syed, Klaus Knapp, Torsten Wind
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Patent number: 10539322Abstract: A method for determining fatigue lifetime consumption of an engine component, by defining a reference thermal load cycle, the reference thermal load cycle being characterized by a reference load cycle amplitude and a reference load cycle time, and determining a reference load cycle lifetime consumption. The method includes measuring a temperature of the engine component, determining a thermal load cycle based upon the temperature measurement, determining a load cycle amplitude, determining a load cycle time, relating the load cycle time to the reference load cycle time, thereby determining a load cycle time factor, relating the load cycle amplitude to the reference load cycle amplitude, thereby determining a load cycle amplitude factor, combining the load cycle time factor and the load cycle amplitude factor into a combined load cycle factor for determining a load cycle lifetime consumption.Type: GrantFiled: April 7, 2017Date of Patent: January 21, 2020Assignee: Ansaldo Energia Switzerland AGInventors: Felipe Bolaños-Chaverri, Torsten Wind, Fernando Biagioli, Khawar Syed
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Publication number: 20180372318Abstract: A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.Type: ApplicationFiled: May 14, 2018Publication date: December 27, 2018Inventors: Felipe BOLANOS, Torsten WIND, Fernando BIAGIOLI
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Publication number: 20180119612Abstract: An exemplary gas turbine power plant includes a gas turbine with a compressor having a compressor inlet. A combustion chamber follows the compressor and a turbine follows the combustion chamber. A cross section of the compressor inlet includes an inner sector and an outer sector in relation to the axis of rotation of the compressor. A plurality of feed ducts introduces oxygen-reduced gas into the inner sector of the compressor inlet. The plurality of feed ducts is arranged in the compressor inlet so as to be distributed in a circumferential direction on a circle concentrically with respect to the axis of the gas turbine.Type: ApplicationFiled: December 29, 2017Publication date: May 3, 2018Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Jaan HELLAT, Eribert Benz, Frank Graf, Torsten Wind, Felix Guethe, Klaus Doebbeling
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Patent number: 9856792Abstract: The invention relates to a method for operating a gas turbine, in which an oxygen-reduced gas and fresh air are delivered to a compressor of the gas turbine in a radially staged manner, the fresh air being delivered via an outer sector of the inlet cross section in relation to the axis of rotation of the compressor, and the oxygen-reduced gas being delivered via an inner sector of the inlet cross section in relation to the axis of rotation of the compressor. The invention relates, further, to a gas turbine power plant with a gas turbine having a compressor inlet which is followed by the flow duct of the compressor and which is divided into an inner sector and an outer sector, a feed for an oxygen-reduced gas being connected to the inner sector of the compressor inlet, and a fresh air feed being connected to the outer sector of the compressor inlet.Type: GrantFiled: August 25, 2014Date of Patent: January 2, 2018Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Jaan Hellat, Eribert Benz, Frank Graf, Torsten Wind, Felix Guethe, Klaus Doebbeling
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Publication number: 20170292695Abstract: A method for determining fatigue lifetime consumption of an engine component, by defining a reference thermal load cycle, the reference thermal load cycle being characterized by a reference load cycle amplitude and a reference load cycle time, and determining a reference load cycle lifetime consumption. The method includes measuring a temperature of the engine component, determining a thermal load cycle based upon the temperature measurement, determining a load cycle amplitude, determining a load cycle time, relating the load cycle time to the reference load cycle time, thereby determining a load cycle time factor, relating the load cycle amplitude to the reference load cycle amplitude, thereby determining a load cycle amplitude factor, combining the load cycle time factor and the load cycle amplitude factor into a combined load cycle factor for determining a load cycle lifetime consumption.Type: ApplicationFiled: April 7, 2017Publication date: October 12, 2017Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Felipe BOLAÑOS-CHAVERRI, Torsten WIND, Fernando BIAGIOLI, Khawar SYED
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Publication number: 20160252251Abstract: The invention refers to a method and a device for flame stabilization in a burner system of a stationary combustion engine, preferably a stationary gas turbine, in which a flow of an air/fuel mixture is produced and being swirled to form a vortex flow to which a swirl number is assignable before entering a combustion zone in which the vortex flow of the air/fuel mixture is ignited to form a flame within a reverse flow zone caused by vortex breakdown. The swirl number perturbation driven by thermoacoustic oscillation inside the burner system is controlled by affecting the vortex flow actively before entering the combustion zone on basis of changing a flame transfer function assigned to the burner system with the proviso of minimizing pulsation amplitudes of the flame transfer function.Type: ApplicationFiled: February 22, 2016Publication date: September 1, 2016Applicant: General Electric Technology GmbHInventors: Fernando BIAGIOLI, Alessandro SCARPATO, Torsten WIND, Khawar SYED
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Publication number: 20160061114Abstract: The invention relates to a method for controlling a gas turbine, operating with an integral fuel reactivity measurement concept. In order to fast determine a safe operation range of the gas turbine with respect to flashback and blow-out, the method includes deducing the fuel composition and therefore the fuel reactivity by combined measurements of (n?1) physico-chemical properties of a fuel mixture with n>1 fuel components, for deriving the concentration of one component for each physico-chemical property of the fuel gas mixture or for determining of a ratio of the fuels with known compositions and adjusting at least one operation parameter of the gas turbine at least partially based on the determined property of the fuel gas mixture entering the combustors. With the technical solution of the present invention, by way of detecting fast changes in fuel gas, it is assured that the gas turbine may operate with varieties of fuel gas under optimized performance and in safe operation ranges.Type: ApplicationFiled: August 26, 2015Publication date: March 3, 2016Inventors: Felix GUETHE, Torsten Wind, Hanspeter Zinn, Michael KLEEMANN
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Publication number: 20140360199Abstract: The invention relates to a method for operating a gas turbine, in which an oxygen-reduced gas and fresh air are delivered to a compressor of the gas turbine in a radially staged manner, the fresh air being delivered via an outer sector of the inlet cross section in relation to the axis of rotation of the compressor, and the oxygen-reduced gas being delivered via an inner sector of the inlet cross section in relation to the axis of rotation of the compressor. The invention relates, further, to a gas turbine power plant with a gas turbine having a compressor inlet which is followed by the flow duct of the compressor and which is divided into an inner sector and an outer sector, a feed for an oxygen-reduced gas being connected to the inner sector of the compressor inlet, and a fresh air feed being connected to the outer sector of the compressor inlet.Type: ApplicationFiled: August 25, 2014Publication date: December 11, 2014Inventors: Jaan HELLAT, Eribert Benz, Frank Graf, Torsten Wind, Felix Guethe, Klaus Doebbeling
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Publication number: 20140305128Abstract: A combustion chamber including a body with a fuel supply duct for supplying a fuel into the body and a carrier air supply duct for supplying air into the body. An adjusting system adjusts the carrier air mass flow supplied into the body according to the features of the fuel.Type: ApplicationFiled: April 4, 2014Publication date: October 16, 2014Inventors: Madhavan Narasimhan POYYAPAKKAM, Khawar Syed, Klaus Knapp, Torsten Wind