Patents by Inventor Johannes Buss
Johannes Buss 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: 9726377Abstract: The burner (1) of a gas turbine includes a duct (2) which houses four vortex generators (3) and a lance (7) that carries one or more nozzles (8) for injecting a fuel within the duct (2). The lance (7) extends from one of the vortex generators (3).Type: GrantFiled: March 9, 2010Date of Patent: August 8, 2017Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Andrea Ciani, Johannes Buss
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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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Patent number: 8943831Abstract: The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles.Type: GrantFiled: June 22, 2011Date of Patent: February 3, 2015Assignee: Alstom Technology LtdInventors: Adnan Eroglu, Johannes Buss, Andrea Ciani
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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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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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Patent number: 8522527Abstract: A burner (1) for a gas turbine includes a duct (2) enclosing a plurality of vortex generators (3) and, downstream of them, a lance (5) provided with nozzles (6) for injecting a gaseous fuel. The burner (1) also includes a mixer (7) for diluting and mixing the gaseous fuel with air to form a mixture. The mixer (7) is connected to the nozzles (6) for feeding them with the mixture. A method includes feeding the gaseous fuel in the burner (1).Type: GrantFiled: January 20, 2010Date of Patent: September 3, 2013Assignee: ALSTOM Technology Ltd.Inventors: Adnan Eroglu, Douglas Anthony Pennell, Johannes Buss, Richard Smith
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Publication number: 20120055162Abstract: The lance of a burner includes a body that defines a first duct with first nozzles for injecting a liquid fuel and a second duct with second nozzles for injecting a gaseous fuel. Outlets of the first nozzles are spaced apart from outlets of the second nozzles. The body includes a third duct with third and fourth nozzles for injecting air. The third nozzles surround an axis of the first nozzles and the fourth nozzles surround an axis of the second nozzles.Type: ApplicationFiled: June 22, 2011Publication date: March 8, 2012Applicant: ALSTOM Technology LtdInventors: Adnan EROGLU, Johannes Buss, Andrea Ciani
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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: 20100287940Abstract: The burner (1) of a gas turbine includes a duct (2) which houses four vortex generators (3) and a lance (7) that carries one or more nozzles (8) for injecting a fuel within the duct (2). The lance (7) extends from one of the vortex generators (3).Type: ApplicationFiled: March 9, 2010Publication date: November 18, 2010Inventors: Andrea Ciani, Johannes Buss
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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
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Publication number: 20100192591Abstract: A burner (1) for a gas turbine includes a duct (2) enclosing a plurality of vortex generators (3) and, downstream of them, a lance (5) provided with nozzles (6) for injecting a gaseous fuel. The burner (1) also includes a mixer (7) for diluting and mixing the gaseous fuel with air to form a mixture. The mixer (7) is connected to the nozzles (6) for feeding them with the mixture. A method includes feeding the gaseous fuel in the burner (1).Type: ApplicationFiled: January 20, 2010Publication date: August 5, 2010Inventors: Adnan Eroglu, Douglas Anthony Pennell, Johannes Buss, Richard Smith
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Patent number: 6247299Abstract: A description is given of a method for feeding liquid and/or gaseous fuels to gas turbines, by means of which method the same feed path to the burner of the gas turbine can be used for both fuels, the liquid fuel being processed before being fed to the burner. This processing takes place in a fuel pre-evaporator which, for the purpose of processing the liquid fuel, has an evaporator tube 2, which is made of a material with good thermal conductivity, interacts with a heating device (3) and, at its one end, is connected to a feed device (4) for a flushing gas, and, at its other end, is connected to a fuel feed and discharge appliance (5).Type: GrantFiled: November 17, 1997Date of Patent: June 19, 2001Assignee: ABB Research Ltd.Inventors: Johannes Buss, Klaus Döbbeling, Dieter Winkler