Patents by Inventor Igor Petrovich Sidko
Igor Petrovich Sidko 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: 10788212Abstract: A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.Type: GrantFiled: January 11, 2016Date of Patent: September 29, 2020Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Jonathan Kay Allen, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Bradford David Borchert, Michael V. Kazakis, Igor Petrovich Sidko
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Patent number: 10480792Abstract: A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.Type: GrantFiled: March 2, 2016Date of Patent: November 19, 2019Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Ilya Aleksandrovich Slobodyanskiy, Igor Petrovich Sidko, Derrick Walter Simons
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Patent number: 10316746Abstract: A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.Type: GrantFiled: February 3, 2016Date of Patent: June 11, 2019Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Jonathan Kay Allen, Bradford David Borchert, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Almaz Valeev, Igor Petrovich Sidko, Matthew Eugene Roberts, Leonid Yul'evich Ginesin
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Patent number: 10253690Abstract: A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.Type: GrantFiled: February 3, 2016Date of Patent: April 9, 2019Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Jonathan Kay Allen, Bradford David Borchert, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Almaz Valeev, Igor Petrovich Sidko, Andrey Pavlovich Subbota
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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: 10094566Abstract: A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.Type: GrantFiled: February 2, 2016Date of Patent: October 9, 2018Assignees: General Electric Company, ExxonMobil Upstream Research CompanyInventors: Bradford David Borchert, Jesse Edwin Trout, Scott Robert Simmons, Almaz Valeev, Ilya Aleksandrovich Slobodyanskiy, Igor Petrovich Sidko, Leonid Yul'evich Ginesin
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Publication number: 20160258629Abstract: A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.Type: ApplicationFiled: March 2, 2016Publication date: September 8, 2016Inventors: Ilya Aleksandrovich Slobodyanskiy, Igor Petrovich Sidko, Derrick Walter Simons
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Publication number: 20160222883Abstract: A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.Type: ApplicationFiled: February 3, 2016Publication date: August 4, 2016Inventors: Jonathan Kay Allen, Bradford David Borchert, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Almaz Valeev, Igor Petrovich Sidko, Andrey Pavlovich Subbota
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Publication number: 20160222884Abstract: A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.Type: ApplicationFiled: February 3, 2016Publication date: August 4, 2016Inventors: Jonathan Kay Allen, Bradford David Borchert, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Almaz Valeev, Igor Petrovich Sidko, Matthew Eugene Roberts, Leonid Yulk'evich Ginesin
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Publication number: 20160223202Abstract: A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.Type: ApplicationFiled: February 2, 2016Publication date: August 4, 2016Inventors: Bradford David Borchert, Jesse Edwin Trout, Scott Robert Simmons, Almaz Valeev, Ilya Aleksandrovich Slobodyanskiy, Igor Petrovich Sidko, Leonid Yul'evich Ginesin
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Publication number: 20160201916Abstract: A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.Type: ApplicationFiled: January 11, 2016Publication date: July 14, 2016Inventors: Jonathan Kay Allen, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Bradford David Borchert, Michael V. Kazakis, Igor Petrovich Sidko
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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