Patents by Inventor Felipe BOLANOS
Felipe BOLANOS 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: 11371699Abstract: A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.Type: GrantFiled: November 12, 2019Date of Patent: June 28, 2022Assignee: General Electric CompanyInventors: Felipe Bolanos Chaverri, Dariusz Oliwiusz Palys, Andre Theuer, Jeffrey De Jonge
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Patent number: 11174792Abstract: A rotary machine includes at least one burner including a front panel having a front side and an opposing back side. The acoustic damper includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one baffle. The wall extends from the back side of the front panel and defines a dampening chamber. The cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The baffle extends from the back side of the front panel and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.Type: GrantFiled: May 21, 2019Date of Patent: November 16, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Fernando Biagioli, Nikola Vranjic, Philipp Brunner, Felipe Bolanos, Dariusz Oliwiusz Palys
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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 -
Publication number: 20210140638Abstract: A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.Type: ApplicationFiled: November 12, 2019Publication date: May 13, 2021Inventors: Felipe Bolanos Chaverri, Dariusz Oliwiusz Palys, Andre Theuer, Jeffrey De Jonge
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Publication number: 20200370477Abstract: A rotary machine includes at least one burner including a front panel having a front side and an opposing back side. The acoustic damper includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one baffle. The wall extends from the back side of the front panel and defines a dampening chamber. The cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The baffle extends from the back side of the front panel and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.Type: ApplicationFiled: May 21, 2019Publication date: November 26, 2020Inventors: Fernando Biagioli, Nikola Vranjic, Philipp Brunner, Felipe Bolanos, Dariusz Oliwiusz Palys
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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: 20180010528Abstract: A method for controlling a gas turbine assembly includes: a compressor in which compression of the outside air occurs for producing a flow of compressed air; a sequential combustor including a first combustor, in which combustion of a mixture of fuel and compressed air arriving from the compressor occurs for producing a flow of hot gasses, and a second combustor which is located downstream of the first combustor and in which combustion of a mixture of fuel and hot gasses arriving from the first combustor occurs; an intermediate turbine in which a partial expansion of the hot gasses arriving from the first combustor occurs; and a second combustor in which combustion of a mixture of fuel and hot gasses arriving from the intermediate turbine occurs; the method further includes, on a start-up transient operating phase of the gas turbine assembly, the step of controlling the fuel mass flow-rate supplied to the first and/or the second combustor on the basis of the flame temperature inside the first combustor.Type: ApplicationFiled: July 5, 2017Publication date: January 11, 2018Applicant: ANSALDO ENERGIA IP UK LIMITEDInventors: Felipe BOLAÑOS-CHAVERRI, Thiemo MEEUWISSEN, Teresa Ernesto MARCHIONE
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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