Patents by Inventor Almaz Valeev
Almaz Valeev 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: 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: 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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Patent number: 9964043Abstract: The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the primary fuel, a water passage, a number of secondary fuel injection ports, and a secondary fuel evaporator system for atomizing the secondary fuel.Type: GrantFiled: November 11, 2014Date of Patent: May 8, 2018Assignee: General Electric CompanyInventors: Geoffrey David Myers, Borys Shershnyov, Andrey Subbota, Alexey Yurievich Gerasimov, Natalya Igorevna Vyazemskaya, Almaz Valeev
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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: 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: 20160169110Abstract: The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the primary fuel, a water passage, a number of secondary fuel injection ports, and a secondary fuel evaporator system for atomizing the secondary fuel.Type: ApplicationFiled: November 11, 2014Publication date: June 16, 2016Inventors: GEOFFREY DAVID MYERS, BORYS SHERSHNYOV, ANDREY SUBBOTA, ALEXEY YURIEVICH GERASIMOV, NATALYA IGOREVNA VYAZEMSKAYA, ALMAZ VALEEV
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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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Patent number: 8991187Abstract: The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.Type: GrantFiled: October 11, 2010Date of Patent: March 31, 2015Assignee: General Electric CompanyInventors: Michael John Hughes, Jonathan Dwight Berry, Jason Thurman Stewart, Almaz Valeev, Chunyang Wu
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Patent number: 8438852Abstract: A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.Type: GrantFiled: April 6, 2010Date of Patent: May 14, 2013Assignee: General Electric CompanyInventors: Almaz Valeev, Chunyang Wu, Leonid Borisovich Zvedenuk
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Patent number: 8418468Abstract: A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.Type: GrantFiled: April 6, 2010Date of Patent: April 16, 2013Assignee: General Electric CompanyInventors: Kevin Weston McMahan, Almaz Valeev, Chunyang Wu
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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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Publication number: 20120085100Abstract: The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.Type: ApplicationFiled: October 11, 2010Publication date: April 12, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Michael John Hughes, Jonathan Dwight Berry, Jason Thurman Stewart, Almaz Valeev, Chunyang Wu
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Publication number: 20120031098Abstract: A fuel nozzle for turbine engine includes a cooling shroud located at the downstream end of the fuel nozzle to help cool the downstream end of the fuel nozzle. The cooling shroud surrounds the exterior circumference of the downstream end of the fuel nozzle. A flow of air is admitted into the cooling shroud and the flow of air travels in the downstream direction through a first passageway which covers the exterior of the fuel nozzle. The cooling air flow then turns 180° and travels in the upstream direction through a second passageway which is located concentrically outside the first passageway. The airflow then leaves the upstream end of the cooling shroud and enters the interior of the fuel nozzle.Type: ApplicationFiled: August 3, 2011Publication date: February 9, 2012Inventors: Leonid Ginessin, Borys Shershnyov, Almaz Valeev
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Publication number: 20110239652Abstract: A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.Type: ApplicationFiled: April 6, 2010Publication date: October 6, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Kevin Weston McMahan, Almaz Valeev, Chunyang Wu
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Publication number: 20110239653Abstract: A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.Type: ApplicationFiled: April 6, 2010Publication date: October 6, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Almaz Valeev, Chunyang Wu, Leonid Borisovich Zvedenuk
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Publication number: 20110214428Abstract: A venturi device for a turbine combustor includes a substantially annular outer liner; a substantially annular inner liner; a venturi channel located between the substantially annular outer and inner liners; the substantially annular outer and inner liners being substantially V-shaped in axial cross-section, thereby defining a throat region; the substantially annular outer liner formed with an array of impingement holes and the substantially annular inner liner formed with a plurality of vortex generators facing the substantially annular outer liner.Type: ApplicationFiled: November 2, 2010Publication date: September 8, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Borys SHERSHNYOV, Leonid GINESSIN, Almaz VALEEV KAMILEVICH
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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