Patents by Inventor Nishant Govindbhai Parsania
Nishant Govindbhai Parsania 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: 9803864Abstract: A turbine combustor section has a flow conditioner including a plurality of conduits arranged to convey pressurized air to an air chamber for entrance into a plurality of fuel nozzles. Each conduit includes an inlet configured to receive the pressurized air from an annular passage and an outlet configured to deliver the pressurized air to the air chamber. A cross-sectional area of each conduit varies between the inlet and the outlet so as to reduce a pressure drop across the flow conditioner.Type: GrantFiled: June 24, 2014Date of Patent: October 31, 2017Assignee: General Electric CompanyInventors: Arjun Singh, Chandrasekhar Pushkaran, Nishant Govindbhai Parsania
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Patent number: 9739201Abstract: A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole.Type: GrantFiled: May 8, 2013Date of Patent: August 22, 2017Assignee: General Electric CompanyInventors: Chandrasekhar Pushkaran, Nishant Govindbhai Parsania, Arjun Singh
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Patent number: 9322553Abstract: A wake manipulating structure for a turbine system includes a combustor liner defining a combustor chamber. Also included is an airflow path located along an outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is a venturi structure or section disposed in the airflow path configured to reduce the wake region.Type: GrantFiled: May 8, 2013Date of Patent: April 26, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Nishant Govindbhai Parsania, Chandrasekhar Pushkaran
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Publication number: 20150369488Abstract: A turbine combustor section has a flow conditioner including a plurality of conduits arranged to convey pressurized air to an air chamber for entrance into a plurality of fuel nozzles. Each conduit includes an inlet configured to receive the pressurized air from an annular passage and an outlet configured to deliver the pressurized air to the air chamber. A cross-sectional area of each conduit varies between the inlet and the outlet so as to reduce a pressure drop across the flow conditioner.Type: ApplicationFiled: June 24, 2014Publication date: December 24, 2015Inventors: Arjun SINGH, Chandrasekhar PUSHKARAN, Nishant Govindbhai PARSANIA
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Patent number: 9217570Abstract: An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings.Type: GrantFiled: January 20, 2012Date of Patent: December 22, 2015Assignee: General Electric CompanyInventors: Nishant Govindbhai Parsania, Geoffrey D. Myers, Gregory Allen Boardman
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Publication number: 20150338101Abstract: A turbomachine combustor includes a combustor body extending from a head end to a discharge end. The combustor body includes a combustor liner defining a combustion chamber. A combustor sleeve surrounds the combustor liner. The combustor sleeve is spaced from the combustor liner forming a passage. The combustor sleeve includes at least one opening. A baffle is arranged in the passage. The baffle includes a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body. The baffle is configured and disposed to compress a fluid flow passing through the passage toward the head end.Type: ApplicationFiled: May 21, 2014Publication date: November 26, 2015Applicant: General Electric CompanyInventors: Nishant Govindbhai Parsania, Chandrasekhar Pushkaran
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Patent number: 9046262Abstract: In an embodiment, a system includes a turbine fuel nozzle having a hub with an axis, a shroud surrounding the hub along the axis, an air flow path between the hub and the shroud, and a fuel flow path. The turbine fuel nozzle also includes a swirl vane extending between the hub and the shroud in a radial direction relative to the axis. The swirl vane includes a fuel inlet coupled to the fuel flow path, a fuel chamber extending from the fuel inlet, and a plurality of fuel outlets extending from the fuel chamber to the air flow path. The plurality of fuel outlets is positioned at an axial distance of at least approximately ? of an axial length of the fuel chamber downstream from an upstream point along an upstream edge of the fuel chamber.Type: GrantFiled: June 27, 2011Date of Patent: June 2, 2015Assignee: General Electric CompanyInventors: Kwanwoo Kim, Nishant Govindbhai Parsania, Ajay Pratap Singh
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Patent number: 8899975Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.Type: GrantFiled: November 4, 2011Date of Patent: December 2, 2014Assignee: General Electric CompanyInventors: Abdul Rafey Khan, Bradley Donald Crawley, Rajendra Paniharam, Nishant Govindbhai Parsania
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Publication number: 20140331674Abstract: A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole.Type: ApplicationFiled: May 8, 2013Publication date: November 13, 2014Applicant: General Electric CompanyInventors: Chandrasekhar Pushkaran, Nishant Govindbhai Parsania, Arjun Singh
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Publication number: 20140331681Abstract: A wake manipulating structure for a turbine system includes a combustor liner defining a combustor chamber. Also included is an airflow path located along an outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is a venturi structure or section disposed in the airflow path configured to reduce the wake region.Type: ApplicationFiled: May 8, 2013Publication date: November 13, 2014Applicant: General Electric CompanyInventors: Nishant Govindbhai Parsania, Chandrasekhar Pushkaran
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Patent number: 8850822Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub having an axis, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple vanes extending between the hub and the shroud, and a first fuel path leading to multiple first fuel outlets disposed on the multiple vanes. The fuel nozzle also includes a second fuel path leading to multiple second fuel outlets disposed on at least one of the hub and/or the shroud, wherein the multiple second fuel outlets are disposed at an axial distance upstream from a downstream end of the hub.Type: GrantFiled: January 24, 2011Date of Patent: October 7, 2014Assignee: General Electric CompanyInventors: Nishant Govindbhai Parsania, Ajay Pratap Singh
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Patent number: 8683804Abstract: In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.Type: GrantFiled: November 13, 2009Date of Patent: April 1, 2014Assignee: General Electric CompanyInventors: Gregory Allen Boardman, David Martin Johnson, Ronald James Chila, Nishant Govindbhai Parsania, Hasan Karim, Joseph Citeno
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Patent number: 8590311Abstract: An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define a ring-like, annular path for the flow of fuel between the two hollow cylinders in each mixing tube, a plurality of air injection slots formed in the concentric hollow cylinders defining corresponding air flow paths from the outside into the interior of each mixing tube, and one or more fuel injection ports formed in selected ones of the plurality of air injection slots that allow for the flow of fuel from the annular path formed by the hollow cylinders into the air flow path, resulting in significantly better mixing and improved thermodynamic behavior of the fuel and air mixture downstream of the nozzle and upstream of the combustor.Type: GrantFiled: April 28, 2010Date of Patent: November 26, 2013Assignee: General Electric CompanyInventors: Nishant Govindbhai Parsania, Gregory Allen Boardman
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Publication number: 20130186094Abstract: An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings.Type: ApplicationFiled: January 20, 2012Publication date: July 25, 2013Inventors: Nishant Govindbhai Parsania, Geoffrey D. Myers, Gregory Allen Boardman
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Publication number: 20130180248Abstract: An apparatus for premixing fuel and air prior to combustion in a gas turbine engine includes an annular fuel passage receiving fuel from a fuel source. The annular fuel passage includes a fuel plenum and has a wave shape with a peak section surrounded by trough sections. An annular air passage surrounds the annular fuel passage. The annular air passage receives air to be mixed with the fuel in the fuel passage for downstream combustion. A plurality of swirler vanes are disposed in the annular air passage adjacent the fuel plenum.Type: ApplicationFiled: January 18, 2012Publication date: July 18, 2013Inventors: Nishant Govindbhai Parsania, Ajay Pratap Singh
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Publication number: 20130115566Abstract: A combustor having wake air injection is provided. The combustor includes a fuel nozzle, first and second vessels formed and disposed to define a flow path along which a first fluid flows in first and second opposite directions toward the fuel nozzle, a vane disposed in the flow path and an injector to inject a second fluid into wake formed by an obstruction disposed in the flow path upstream from the vane.Type: ApplicationFiled: November 4, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Abdul Rafey Khan, Bradley Donald Crawley, Rajendra Paniharam, Nishant Govindbhai Parsania
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Patent number: 8418469Abstract: A fuel nozzle assembly is disclosed. The fuel nozzle assembly comprises an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween. The fuel nozzle assembly further comprises a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus. The fuel nozzle assembly further comprises an air injection feature configured to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube.Type: GrantFiled: September 27, 2010Date of Patent: April 16, 2013Assignee: General Electric CompanyInventors: Geoffrey David Myers, Nishant Govindbhai Parsania, Gregory Allen Boardman
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Publication number: 20130047619Abstract: An injection nozzle assembly includes a nozzle body having an outer surface and an inner surface that defines a flow passage, and a center body arranged within the nozzle body and extending along the flow passage. The center body includes a first end that extends to a tip portion through an intermediate portion that defines a fluid passage. The intermediate portion includes a first outer dimension and the tip portion includes a second outer dimension that is distinct from the first outer dimension. The center body includes a plurality of grooves that extend axially along the tip portion.Type: ApplicationFiled: August 30, 2011Publication date: February 28, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Kwanwoo Kim, Nishant Govindbhai Parsania
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Publication number: 20120324896Abstract: In an embodiment, a system includes a turbine fuel nozzle having a hub with an axis, a shroud surrounding the hub along the axis, an air flow path between the hub and the shroud, and a fuel flow path. The turbine fuel nozzle also includes a swirl vane extending between the hub and the shroud in a radial direction relative to the axis. The swirl vane includes a fuel inlet coupled to the fuel flow path, a fuel chamber extending from the fuel inlet, and a plurality of fuel outlets extending from the fuel chamber to the air flow path. The plurality of fuel outlets is positioned at an axial distance of at least approximately ? of an axial length of the fuel chamber downstream from an upstream point along an upstream edge of the fuel chamber.Type: ApplicationFiled: June 27, 2011Publication date: December 27, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Kwanwoo Kim, Nishant Govindbhai Parsania, Ajay Pratap Singh
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Publication number: 20120186255Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub having an axis, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple vanes extending between the hub and the shroud, and a first fuel path leading to multiple first fuel outlets disposed on the multiple vanes. The fuel nozzle also includes a second fuel path leading to multiple second fuel outlets disposed on at least one of the hub and/or the shroud, wherein the multiple second fuel outlets are disposed at an axial distance upstream from a downstream end of the hub.Type: ApplicationFiled: January 24, 2011Publication date: July 26, 2012Applicant: General Electric CompanyInventors: Nishant Govindbhai Parsania, Ajay Pratap Singh