Patents by Inventor Michael Düsing
Michael Düsing 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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Publication number: 20150226122Abstract: The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop. The disclosure further refers to a method for operating a gas turbine with such a combustor arrangement.Type: ApplicationFiled: April 22, 2015Publication date: August 13, 2015Inventors: Michael DUESING, Luis TAY WO CHONG HILARES, Mirko Ruben BOTHIEN, Jaan HELLAT, Bruno SCHUERMANS
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Publication number: 20150198334Abstract: The invention refers to a sequential combustor arrangement including a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, and a second burner for admixing a second fuel and a second combustion chamber. To assure good mixing over a wide operating range, the ratio of the pressure loss of the first combustor to the pressure loss of the dilution gas admixer is in the range of 1 to 6. The invention further refers to a gas turbine including such a sequential combustor arrangement as well as method for operating a gas turbine with such a sequential combustor arrangement.Type: ApplicationFiled: January 9, 2015Publication date: July 16, 2015Inventors: Michael DUESING, Ewald FREITAG
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Patent number: 9057518Abstract: A reheat burner (1) includes a channel (2) with a lance (3) protruding thereinto to inject a fuel over an injection plane (4) perpendicular to a channel longitudinal axis (15). The channel (2) and lance (3) define a vortex generation zone (6) upstream of the injection plane (4) and a mixing zone (9) downstream of the injection plane (4) in the hot gas (G) direction. The mixing zone (9) includes a high speed area (16) with a constant cross section, and a diffusion area (17) with a flared cross section downstream of the high speed area (16) in the hot gas (G) direction.Type: GrantFiled: August 2, 2011Date of Patent: June 16, 2015Assignee: ALSTOM TECHNOLOGY LTD.Inventors: Johannes Buss, Andrea Ciani, Adnan Eroglu, Urs Benz, Michael Düsing, Michael Hutapea
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Patent number: 9046265Abstract: A reheat burner includes a channel with a lance projecting thereinto to inject a fuel over an injection plane perpendicular to a channel longitudinal axis. The channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas direction. The mixing zone has a cross section with diverging side walls in the hot gas direction. The diverging side walls define curved surfaces in the hot gas direction having a constant radius.Type: GrantFiled: August 8, 2011Date of Patent: June 2, 2015Assignee: ALSTOM TECHNOLOGY LTDInventors: Johannes Buss, Andrea Ciani, Urs Benz, Michael Düsing, Michael Hutapea, Adnan Eroglu
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Publication number: 20150101341Abstract: The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially includes at least one compressor, a first combustor which is connected downstream to the compressor. The hot gases of the first combustor are admitted at least to an intermediate turbine or directly or indirectly to a second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery. At least one combustor runs under a caloric combustion path having a can-architecture, and wherein the air ratio (?) of the combustion at least of the second combustor is kept below a maximum air ratio (?max).Type: ApplicationFiled: December 19, 2014Publication date: April 16, 2015Inventors: Michael DÜSING, Adnan EROGLU
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Publication number: 20150047365Abstract: The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a dilution burner for admixing a dilution gas and a second fuel via a dilution-gas-fuel-admixer to the first combustor combustion products. The dilution-gas-fuel-admixer has at least one streamlined body which is arranged in the dilution burner for introducing the at least one second fuel into the dilution burner through at least one fuel nozzle, and which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the dilution burner. The streamlined body includes a dilution gas opening for admixing dilution gas into the first combustor combustion products upstream of the at least one fuel nozzle. The disclosure further refers to a method for operating a gas turbine with such a sequential combustor arrangement.Type: ApplicationFiled: July 29, 2014Publication date: February 19, 2015Inventor: Michael DUESING
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Patent number: 8938968Abstract: An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052.Type: GrantFiled: December 18, 2009Date of Patent: January 27, 2015Assignee: Alstom Technology Ltd.Inventors: Johannes Buss, Andrea Ciani, Michael Düsing, Adnan Eroglu
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Publication number: 20150007547Abstract: The combustion device includes a burner, a combustion chamber downstream of the burner, a lance projecting into the burner for fuel and air injection, and a plenum that at least partly houses the burner. The plenum is connected to the inside of the lance to supply an oxidiser to it.Type: ApplicationFiled: September 19, 2014Publication date: January 8, 2015Inventors: Michael DUESING, Andrea Ciani, Adnan Eroglu
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Patent number: 8850788Abstract: The burner (1) for a gas turbine includes a duct (2) housing a plurality of tetrahedron shaped vortex generators (3) and a lance (4) to inject a fuel to be combusted. Within the duct (2), a plurality of vortex generators (3) are provided with a plurality of holes (9) for injecting cooling air. The cooling holes (9) define passing through areas that are non-uniformly distributed on a top wall (11) of the vortex generators (3). A method for locally cooling a hot gases flow passing through a burner includes non-uniformly injecting cooling air from a vortex generator into the hot gas flow in the duct, which can reduce the occurrence of flashback in the burner.Type: GrantFiled: March 10, 2010Date of Patent: October 7, 2014Assignee: Alstom Technology LtdInventors: Adnan Eroglu, Andrea Ciani, Johannes Buss, Michael Düsing, Urs Benz
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Publication number: 20140109578Abstract: The disclosure relates to a combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension, which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper.Type: ApplicationFiled: October 24, 2013Publication date: April 24, 2014Applicant: Alstom Technology LtdInventors: Mirko Ruben BOTHIEN, Michael Düsing
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Publication number: 20140109579Abstract: The disclosure relates combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and an downstream end adapted for connection to a first stage of a turbine, wherein the downstream end comprises an outer wall, an inner wall, a first and a second side wall. The combustor transition is, characterized in that at least one side wall has a side wall extension, which is extending in a downstream direction beyond the outlet. Besides the combustor transition a gas turbine includes such a combustor transition, a method for retrofitting a gas turbine with such a combustor transition as well as a method for borescope inspection of a GT with such a combustor transition are disclosed.Type: ApplicationFiled: October 24, 2013Publication date: April 24, 2014Applicant: ALSTOM Technology LtdInventors: Michael DÜSING, Mirko Ruben BOTHIEN
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Publication number: 20140026586Abstract: The invention refers to a reheat burner that includes a flow channel for a hot gas flow with a lance arranged along said flow channel, protruding into the flow channel for injecting a fuel over an injection plane perpendicular to a channel longitudinal axis, wherein the channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas flow direction. The mixing zone provides at least one axially region having different cross sectional areas along its longitudinal axis with continuously changing shape, or having non circular cross section areas which change location along its longitudinal axis by continuously rotation around the longitudinal axis.Type: ApplicationFiled: July 26, 2013Publication date: January 30, 2014Applicant: ALSTOM Technology LtdInventor: Michael Düsing
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Publication number: 20120047901Abstract: A reheat burner includes a channel with a lance projecting thereinto to inject a fuel over an injection plane perpendicular to a channel longitudinal axis. The channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream of the injection plane in the hot gas direction. The mixing zone has a cross section with diverging side walls in the hot gas direction. The diverging side walls define curved surfaces in the hot gas direction having a constant radius.Type: ApplicationFiled: August 8, 2011Publication date: March 1, 2012Applicant: ALSTOM Technology Ltd.Inventors: Johannes BUSS, Andrea Ciani, Urs Benz, Michael Düsing, Michael Hutapea, Adnan Eroglu
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Publication number: 20120036824Abstract: A reheat burner (1) includes a channel (2) with a lance (3) protruding thereinto to inject a fuel over an injection plane (4) perpendicular to a channel longitudinal axis (15). The channel (2) and lance (3) define a vortex generation zone (6) upstream of the injection plane (4) and a mixing zone (9) downstream of the injection plane (4) in the hot gas (G) direction. The mixing zone (9) includes a high speed area (16) with a constant cross section, and a diffusion area (17) with a flared cross section downstream of the high speed area (16) in the hot gas (G) direction.Type: ApplicationFiled: August 2, 2011Publication date: February 16, 2012Inventors: Johannes Buss, Andrea Ciani, Adnan Eroglu, Urs Benz, Michael DÜSING, Michael Hutapea
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Publication number: 20100236246Abstract: An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052.Type: ApplicationFiled: December 18, 2009Publication date: September 23, 2010Applicant: ALSTOM Technology LtdInventors: Johannes BUSS, Andrea CIANI, Michael DÜSING, Adnan EROGLU
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Publication number: 20100229570Abstract: The burner (1) for a gas turbine includes a duct (2) housing a plurality of tetrahedron shaped vortex generators (3) and a lance (4) to inject a fuel to be combusted. Within the duct (2), a plurality of vortex generators (3) are provided with a plurality of holes (9) for injecting cooling air. The cooling holes (9) define passing through areas that are non-uniformly distributed on a top wall (11) of the vortex generators (3). A method for locally cooling a hot gases flow passing through a burner includes non-uniformly injecting cooling air from a vortex generator into the hot gas flow in the duct, which can reduce the occurrence of flashback in the burner.Type: ApplicationFiled: March 10, 2010Publication date: September 16, 2010Inventors: Adnan Eroglu, Andrea Ciani, Johannes Buss, Michael Düsing, Urs Benz