Patents by Inventor Sergey Anatolievich Meshkov
Sergey Anatolievich Meshkov 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: 10221762Abstract: A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.Type: GrantFiled: February 28, 2013Date of Patent: March 5, 2019Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Almaz Kamilevich Valeev, Leonid Yul'evich Ginesin, Borys Borysovich Shershnyov, Igor Petrovich Sidko, Sergey Anatolievich Meshkov
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Patent number: 9957888Abstract: A system and method for generating an exhaust syngas are disclosed. The system includes a mixing unit, a heat exchanger, and an engine. The mixing unit is configured to mix a hydrocarbon fuel, an oxidant, and water to generate a fuel mixture. The heat exchanger is coupled to the mixing unit and is configured to receive the fuel mixture from the mixing unit, evaporate the water by heating the fuel mixture using a hot fluid, and generate a heated fuel mixture. The engine is coupled to the heat exchanger and is configured to receive the heated fuel mixture from the heat exchanger and generate an exhaust syngas by partially combusting the heated fuel mixture.Type: GrantFiled: March 30, 2016Date of Patent: May 1, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Vitali Victor Lissianski, Sergey Anatolievich Meshkov, Mathilde Bieber, Vitaly Vladimirovich Kuzminov
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Patent number: 9822649Abstract: An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.Type: GrantFiled: November 12, 2008Date of Patent: November 21, 2017Assignee: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, Jr., Willy Steve Ziminsky, Kevin Weston McMahan, Ronald James Chila, Sergey Anatolievich Meshkov
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Publication number: 20170284295Abstract: A system and method for generating an exhaust syngas are disclosed. The system includes a mixing unit, a heat exchanger, and an engine. The mixing unit is configured to mix a hydrocarbon fuel, an oxidant, and water to generate a fuel mixture. The heat exchanger is coupled to the mixing unit and is configured to receive the fuel mixture from the mixing unit, evaporate the water by heating the fuel mixture using a hot fluid, and generate a heated fuel mixture. The engine is coupled to the heat exchanger and is configured to receive the heated fuel mixture from the heat exchanger and generate an exhaust syngas by partially combusting the heated fuel mixture.Type: ApplicationFiled: March 30, 2016Publication date: October 5, 2017Inventors: Vitali Victor Lissianski, Sergey Anatolievich Meshkov, Mathilde Bieber, Vitaly Vladimirovich Kuzminov
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Patent number: 9297534Abstract: A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones.Type: GrantFiled: July 29, 2011Date of Patent: March 29, 2016Assignee: General Electric CompanyInventors: Joseph Citeno, Dmitry Alexandrovitch Lysenko, Sergey Anatolievich Meshkov, Valery Alexandrovich Mitrofanov, Almaz Valeev
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Publication number: 20160010548Abstract: A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.Type: ApplicationFiled: February 28, 2013Publication date: January 14, 2016Inventors: Almaz Kamilevich Valeev, Leonid Yul'evich Ginesin, Borys Borysovich Shershnyov, Igor Petrovich Sidko, Sergey Anatolievich Meshkov
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Publication number: 20130025289Abstract: A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones.Type: ApplicationFiled: July 29, 2011Publication date: January 31, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Joseph Citeno, Dmitry Alexandrovitch Lysenko, Sergey Anatolievich Meshkov, Valery Alexandrovich Mitrofanov, Almaz Valeev
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Patent number: 8276386Abstract: A combustor includes an end cover and a combustion chamber downstream of the end cover. The combustor further includes nozzles disposed radially in the end cover and a shroud surrounding at least one of the nozzles and extending downstream into the combustion chamber. The shroud includes an inner wall surface and an outer wall surface. A method for operating a combustor includes flowing compressed working fluid through nozzles into a combustion chamber, flowing fuel through each nozzle in a first subset of the nozzles into the combustion chamber, and igniting the fuel from each nozzle in the first subset of nozzles in the combustion chamber. In addition, the method includes extending into the combustion chamber a separate shroud around each nozzle in a second subset of the nozzles and isolating fuel to each nozzle in the second subset of nozzles.Type: GrantFiled: September 24, 2010Date of Patent: October 2, 2012Assignee: General Electric CompanyInventors: Willy Steve Ziminsky, Christopher Edward Wolfe, Sergey Anatolievich Meshkov, Sergey Adolfovich Oskin
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Publication number: 20120073300Abstract: A combustor includes an end cover and a combustion chamber downstream of the end cover. The combustor further includes nozzles disposed radially in the end cover and a shroud surrounding at least one of the nozzles and extending downstream into the combustion chamber. The shroud includes an inner wall surface and an outer wall surface. A method for operating a combustor includes flowing compressed working fluid through nozzles into a combustion chamber, flowing fuel through each nozzle in a first subset of the nozzles into the combustion chamber, and igniting the fuel from each nozzle in the first subset of nozzles in the combustion chamber. In addition, the method includes extending into the combustion chamber a separate shroud around each nozzle in a second subset of the nozzles and isolating fuel to each nozzle in the second subset of nozzles.Type: ApplicationFiled: September 24, 2010Publication date: March 29, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Willy Steve Ziminsky, Christopher Edward Wolfe, Sergey Anatolievich Meshkov, Sergey Adolfovich Oskin
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Patent number: 8037689Abstract: A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.Type: GrantFiled: August 21, 2007Date of Patent: October 18, 2011Assignee: General Electric CompanyInventors: Sergey Adolfovich Oskin, Mark Allan Hadley, Joel Meador Hall, Sergey Konstantinovich Yerokhin, Sergey Anatolievich Meshkov
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Publication number: 20110232299Abstract: An impingement structure 204 in an impingement cooling system, wherein the impingement structure 204 comprises a plurality of impingement apertures 214 that are configured to impinge a flow of coolant and direct resulting coolant jets against a target-surface 210 that opposes the impingement structure 204 across an impingement cavity 212 formed therebetween, the impingement structure 204 comprising a corrugated configuration.Type: ApplicationFiled: March 9, 2011Publication date: September 29, 2011Inventors: Sergey Aleksandrovich Stryapunin, Sergey Anatolievich Meshkov
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Publication number: 20110225948Abstract: Apparatus for providing electromagnetic radiation to a combustor during a combustion process are disclosed. An electromagnetic radiation source delivers electromagnetic radiation through a first waveguide to a second waveguide that includes an electromagnetic radiation outlet positioned to deliver electromagnetic radiation to the interior of the combustor. Electromagnetic radiation is delivered to low temperature regions of a combustor to reduce carbon monoxide (CO) and unburned hydrocarbon (UHC) emissions. In addition, the electromagnetic radiation stimulates the combustion process so that lean air-fuel mixtures and low BTU gases can be burned at lower combustion temperatures leading to reduced NOx emissions.Type: ApplicationFiled: February 28, 2011Publication date: September 22, 2011Inventors: Almaz Kamilevich Valeev, Sergey Adolfovich Oskin, Sergey Anatolievich Meshkov, Valery Alexandrovich Mitrofanov, Dmitry Vladlenovich Tretvakov
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Publication number: 20110197591Abstract: A combustor for a gas turbine includes a plurality of radially outer nozzles arranged in an annular array, each of the radially outer nozzles having an outlet end located to supply fuel and/or air to a first combustion chamber. A center nozzle has an outlet end located axially upstream of the outlet ends of the radially outer nozzles, and is configured and arranged to supply fuel and air to a second combustion chamber axially upstream of the first combustion chamber. The second combustion chamber opens into the first combustion chamber and has a length sufficient to maintain a center nozzle flame confined to the second combustion chamber.Type: ApplicationFiled: February 11, 2011Publication date: August 18, 2011Inventors: Almaz Valeev, Sergey Anatolievich Meshkov, Mark Hadley, Stanley Widener, Geoffrey Myers, Valery Alexandrovich Mitrofanov
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Publication number: 20110173984Abstract: An air bypass band assembly includes a transition piece of a gas turbine, the transition piece having at least one opening therein to allow a flow of air to pass through the at least one opening. The air bypass band assembly also includes a band that is movable between at least two positions, a first one of the at least two positions being a closed position where the at least one opening is closed to prevent the flow of air from flowing through the at least one opening, a second one of the at least two positions being an open where the at least one opening is opened to allow the flow of air to flow through the at least one opening. The air bypass band assembly further includes a mechanism that moves the band between the at least two positions.Type: ApplicationFiled: November 2, 2010Publication date: July 21, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Almaz Valeev, Leonid Ginessin, Sergey Anatolievich Meshkov
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Publication number: 20100192580Abstract: A combustor includes a burner tube that receives fuel for combustion from a fuel delivery system. An axial swirler is installed in the burner tube. The burner tube is flared downstream of the swirler. The structure provides for improved combustion stability while extending lean blowout and low frequency dynamics margins, which in turn serve to further reduce NOx emissions.Type: ApplicationFiled: February 3, 2009Publication date: August 5, 2010Inventors: Derrick Walter Simons, Leonid Zvedenuk, Sergey Anatolievich Meshkov, Valery Mitrofanov
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Publication number: 20100115953Abstract: An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.Type: ApplicationFiled: November 12, 2008Publication date: May 13, 2010Inventors: Lewis Berkley Davis, JR., Willy Steve Ziminsky, Kevin Weston McMahan, Ronald James Chila, Sergey Anatolievich Meshkov
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Publication number: 20090049838Abstract: A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.Type: ApplicationFiled: August 21, 2007Publication date: February 26, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Sergey Adolfovich Oskin, Mark Allan Hadley, Joel Meador Hall, Sergey Konstantinovich Yerokhin, Sergey Anatolievich Meshkov