Patents by Inventor Borys Borysovich Shershnyov
Borys Borysovich Shershnyov 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: 10794589Abstract: A liquid fuel cartridge for a gas turbine fuel nozzle includes a tube having an inlet end and an outlet end with one or more fuel exit orifices; and a homogenizer located within the tube, adjacent and up-stream of the outlet end. The homogenizer is formed by a substantially-cylindrical body open at opposite ends, and a first row of circumferentially-spaced flanges projecting radially outwardly from the substantially cylindrical body, with radially-outer edges of said flanges engaged with an interior surface of the tube thereby creating a plurality of apertures for a liquid fuel and water emulsion. The homogenizer body may also be provided with a plurality of circumferentially-spaced radially-oriented orifices to promote better mixing of the fuel/water emulsion.Type: GrantFiled: November 8, 2013Date of Patent: October 6, 2020Assignee: General Electric CompanyInventors: Borys Borysovich Shershnyov, Alexey Yurievich Gerasimov
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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: 10006636Abstract: A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels.Type: GrantFiled: November 18, 2013Date of Patent: June 26, 2018Assignee: General Electric CompanyInventors: Leonid Yulievich Ginessin, Borys Borysovich Shershnyov
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Publication number: 20170261209Abstract: A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels.Type: ApplicationFiled: November 18, 2013Publication date: September 14, 2017Inventors: Leonid Yulievich GINESSIN, Borys Borysovich SHERSHNYOV
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Publication number: 20170176000Abstract: A liquid fuel cartridge for a gas turbine fuel nozzle includes a tube having an inlet end and an outlet end with one or more fuel exit orifices; and a homogenizer located within the tube, adjacent and up-stream of the outlet end. The homogenizer is formed by a substantially-cylindrical body open at opposite ends, and a first row of circumferentially-spaced flanges projecting radially outwardly from the substantially cylindrical body, with radially-outer edges of said flanges engaged with an interior surface of the tube thereby creating a plurality of apertures for a liquid fuel and water emulsion. The homogenizer body may also be provided with a plurality of circumferentially-spaced radially-oriented orifices to promote better mixing of the fuel/water emulsion.Type: ApplicationFiled: November 8, 2013Publication date: June 22, 2017Inventors: Borys Borysovich SHERSHNYOV, Alexey Yuriech GERASIMOV
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Patent number: 9500372Abstract: A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section.Type: GrantFiled: December 5, 2011Date of Patent: November 22, 2016Assignee: General Electric CompanyInventors: Leonid Yulevich Ginesin, Borys Borysovich Shershnyov, Andrey Pavlovich Subbota, Almaz Kamilevich 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: 20150135716Abstract: A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels.Type: ApplicationFiled: November 18, 2013Publication date: May 21, 2015Applicant: General Electric CompanyInventors: Leonid Yulievich Ginessin, Borys Borysovich Shershnyov
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Publication number: 20150068212Abstract: A combustion liner includes a substantially cylindrical body having forward and aft ends, the forward end provided with plural, circumferentially-shaped stops adapted for connection to a flow sleeve surrounding the substantially cylindrical body. Each stop includes a radially-projecting strut having an end remote from the substantially-cylindrical body provided with a tab having a shape different than the strut. Each strut is received in a slot formed in the flow sleeve, with the tab on an exterior surface of the flow sleeve.Type: ApplicationFiled: April 19, 2012Publication date: March 12, 2015Inventors: Leonid Yulevich Ginesin, Borys Borysovich Shershnyov
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Publication number: 20140345289Abstract: A turbomachine combustor assembly includes a combustor body, a combustion chamber defined within the combustor body, one or more combustion nozzles positioned to direct a combustible fluid into the combustion chamber, and a fuel start-up system fluidly connected to the combustion chamber. The fuel start-up system is configured and disposed to combine a liquid fuel and a combustible gas to form an ignition fuel. A pilot nozzle is fluidly connected to the fuel start-up system. The pilot nozzle is configured and disposed to deliver an atomized cloud of the ignition fuel toward the combustion chamber.Type: ApplicationFiled: February 1, 2012Publication date: November 27, 2014Applicant: General Electric CompanyInventor: Borys Borysovich Shershnyov
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Publication number: 20140260259Abstract: A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section.Type: ApplicationFiled: December 5, 2011Publication date: September 18, 2014Applicant: General Electric CompanyInventors: Leonid Yulevich Ginesin, Borys Borysovich Shershnyov, Andrey Pavlovich Subbota, Almaz Kamilevich Valeev
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Publication number: 20140123671Abstract: A combustor (10) includes a liner (12) that defines a combustion chamber (18) first pre-mix chamber (14) is upstream of the combustion chamber, and a fuel plenum (40) in fluid communication with the first pre-mix chamber surrounds a least a portion of the first pre-mix chamber. A method of supplying a fuel to combustor includes flowing the fuel over an outer surface of a first pre-mix chamber and into the first pre-mix chamber.Type: ApplicationFiled: June 30, 2011Publication date: May 8, 2014Applicant: General Electric CompanyInventors: Borys Borysovich Shershnyov, Geoffrey David Myers, Leonid Yulyevich Ginesin
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Patent number: 8596069Abstract: A combustor section of a gas turbine includes a combustor liner, a sleeve and a fuel-air mixing tube. The combustor liner defines a combustion chamber. The sleeve surrounds the combustor liner. The combustor liner and the sleeve define an annular flow space. The fuel-air mixing tube is configured to channel a mixture of fuel and air and includes an inlet and an outlet. The inlet is in fluid communication with an exterior of the sleeve, and the outlet is in fluid communication with the combustion chamber. The combustor casing encloses the combustor section upstream relative to the inlet of the mixing tube and extends downstream. The sleeve and the combustor casing define a discharge air space. The discharge space is in fluid communication with the mixing tube. The fuel supplying device is located exteriorly of the combustor casing and is configured to inject fuel into the mixing tube.Type: GrantFiled: January 13, 2012Date of Patent: December 3, 2013Assignee: General Electric CompanyInventors: Borys Borysovich Shershnyov, Leonid Yul'evich Ginesin, Krishnakumar Venkataraman
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Publication number: 20130180255Abstract: A combustor section of a gas turbine includes a combustor liner, a sleeve and a fuel-air mixing tube. The combustor liner defines a combustion chamber. The sleeve surrounds the combustor liner. The combustor liner and the sleeve define an annular flow space. The fuel-air mixing tube is configured to channel a mixture of fuel and air and includes an inlet and an outlet. The inlet is in fluid communication with an exterior of the sleeve, and the outlet is in fluid communication with the combustion chamber. The combustor casing encloses the combustor section upstream relative to the inlet of the mixing tube and extends downstream. The sleeve and the combustor casing define a discharge air space. The discharge space is in fluid communication with the mixing tube. The fuel supplying device is located exteriorly of the combustor casing and is configured to inject fuel into the mixing tube.Type: ApplicationFiled: January 13, 2012Publication date: July 18, 2013Applicant: General Electric CompanyInventors: Borys Borysovich Shershnyov, Leonid Yul'evich Ginesin, Krishnakumar Venkataraman