Patents by Inventor Matthew Yaquinto
Matthew Yaquinto 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: 11933231Abstract: A method for tuning a gas turbine engine includes performing a sensitivity step process on a tuning parameter. An operating parameter is monitored. The gas turbine is operating in a first operational state and the operating parameter has an initial condition. The tuning parameter is selected for adjustment. The tuning parameter is adjusted by a predefined amount. The adjustment includes applying an incremental bias adjustment to a fuel flow fraction schedule. The gas turbine engine transitions to a second operational state, wherein the operating parameter has an adjusted condition. The adjusted condition and the initial condition of the operating parameter are applied to a cost function. It is then determined that the cost function results in a cost function value indicative of a decreased cost. The incremental bias adjustment and the cost function value is written to a bias look-up table and are associated with the selected tuning parameter.Type: GrantFiled: February 7, 2022Date of Patent: March 19, 2024Assignee: Power Systems Mfg., LLCInventors: Wenping Wang, Matthew Yaquinto, Nicolas Demougeot, Alex Steinbrenner, Cory Dodson, Jaime Serrano
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Publication number: 20230408097Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A blocker is provided at an outlet portion of each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes and/or the radially inner subset of air/fuel mixing tubes to form a flame anchoring surface.Type: ApplicationFiled: November 3, 2022Publication date: December 21, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Publication number: 20230408094Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of first vanes radially arrayed about a central axis of the injector and a plurality of second vanes radially arrayed about the central axis of the injector and disposed radially inward of the plurality of first vanes. A plurality of fuel injection holes are disposed nearer to a trailing edge than to a leading edge of the second vanes for injecting fuel into compressed air passing through over the second vanes. The trailing edge of each of the second vanes includes a non-planar profile configured to induce turbulence in the compressed air to thereby mix the fuel with the compressed air and reduce the surfaces on which undesirable flame anchoring may occur.Type: ApplicationFiled: November 3, 2022Publication date: December 21, 2023Inventors: Dwain TERREL, Matthew YAQUINTO, Fred HERNANDEZ, Hany RIZKALLA, Nicolas DEMOUGEOT, Peter John STUTTAFORD
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Publication number: 20230408095Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A static air plenum surrounds each of the air/fuel mixing tubes to thermally isolate the air/fuel mixing tube from the respective fuel manifold.Type: ApplicationFiled: November 3, 2022Publication date: December 21, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Publication number: 20230408096Abstract: A combustor of a gas turbine engine is provided with a first injector and a second injector. The first injector surrounds a combustion liner and is positioned at a downstream end of a flow sleeve. A dome plate is positioned to receive a fuel/air mixture from the first injector and turn it 180 degrees to enter a combustion zone formed within the combustion liner. The second injector is positioned radially inward of the combustion liner at an inlet end of the combustion zone and receives only compressed air from the first injector. The second injector includes a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes.Type: ApplicationFiled: November 3, 2022Publication date: December 21, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Publication number: 20230250765Abstract: A method for tuning a gas turbine engine includes performing a sensitivity step process on a tuning parameter. An operating parameter is monitored. The gas turbine is operating in a first operational state and the operating parameter has an initial condition. The tuning parameter is selected for adjustment. The tuning parameter is adjusted by a predefined amount. The adjustment includes applying an incremental bias adjustment to a fuel flow fraction schedule. The gas turbine engine transitions to a second operational state, wherein the operating parameter has an adjusted condition. The adjusted condition and the initial condition of the operating parameter are applied to a cost function. It is then determined that the cost function results in a cost function value indicative of a decreased cost. The incremental bias adjustment and the cost function value is written to a bias look-up table and are associated with the selected tuning parameter.Type: ApplicationFiled: February 7, 2022Publication date: August 10, 2023Inventors: Wenping Wang, Matthew Yaquinto, Nicolas Demougeot, Alex Steinbrenner, Cory Dodson, Jaime Serrano
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Publication number: 20230193839Abstract: A method for extending an operating window of an operating mode of a gas turbine engine includes monitoring operating conditions of the gas turbine engine. The gas turbine engine is prevented by the method from transitioning from the first operating mode up to a second operating mode. A bulk temperature demand of the gas turbine engine is adjusted by a predefined amount to generate a first biased bulk temperature demand. The adjustment includes applying a first incremental bias to a bulk flame temperature schedule. The operation of the gas turbine engine is then adjusted based on the first biased bulk temperature demand. The monitored operating conditions are analyzed to determine whether one of the operating conditions has reached a threshold value.Type: ApplicationFiled: December 17, 2021Publication date: June 22, 2023Inventors: Wenping Wang, Danny Grobbe, Matthew Yaquinto, Jaime Serrano, Franklin van den Hout, Nicolas Demougeot
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Publication number: 20230135396Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. Each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes includes a substantially quadrilateral cross-sectional profile, and each of the air/fuel mixing tubes of the radially inner subset of air/fuel mixing tubes includes a substantially circular cross-sectional profile.Type: ApplicationFiled: November 3, 2022Publication date: May 4, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Patent number: 10739007Abstract: A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.Type: GrantFiled: May 9, 2018Date of Patent: August 11, 2020Assignee: POWER SYSTEMS MFG., LLCInventors: Alfredo Cires, Peter Stuttaford, Matthew Yaquinto, Hany Rizkalla, Khalid Oumejjoud, Fred Hernandez, Bryan Kalb, Nicolas Demougeot, Joshua R McNally, Ramesh Keshava Bhattu, Bernard Tam-Yen Sam
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Publication number: 20190346142Abstract: A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.Type: ApplicationFiled: May 9, 2018Publication date: November 14, 2019Inventors: Alfredo Cires, Peter Stuttaford, Matthew Yaquinto, Hany Rizkalla, Khalid Oumejjoud, Fred Hernandez, Bryan Kalb, Nicolas Demougeot, Joshua R. McNally, Ramesh Keshava Bhattu, Bernard Tam-Yen Sam
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Patent number: 10378456Abstract: The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels.Type: GrantFiled: December 1, 2015Date of Patent: August 13, 2019Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Peter John Stuttaford, Khalid Oumejjoud, Fred Hernandez, Hany Rizkalla, Timothy Hui, Matthew Yaquinto, Jesse Sewell