Patents by Inventor Krishna Kumar Venkataraman
Krishna Kumar Venkataraman 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: 9714768Abstract: A gas turbine engine that includes: a combustor coupled to a turbine and a downstream injection system that includes two injection stages, a first stage and a second stage, positioned within an interior flowpath, wherein the first stage comprises an axial position that is aft of the primary air and fuel injection system and the second stage comprising an axial position that is aft of the first stage. Each of the first stage and the second stage include a plurality of circumferentially spaced injectors, each injector of which is configured to inject air and fuel into a flow through the interior flowpath. The first stage and the second stage have a configuration that limits a fuel injected at the second stage to less than 50% of a fuel injected at the first stage.Type: GrantFiled: March 15, 2013Date of Patent: July 25, 2017Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Kaitlin Marie Graham
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Patent number: 9528439Abstract: A gas turbine engine that includes: an interior flowpath defined through a combustor and a turbine; an aft frame forming an interface between the combustor the turbine, the aft frame comprising a rigid structural member that circumscribes the interior flowpath, wherein the aft frame includes an inner wall that defines an outboard boundary of the interior flowpath; a circumferentially extending fuel plenum formed through the aft frame; and outlet ports formed through the inner wall of the aft frame. The outlet ports may be configured to connect the fuel plenum to the interior flowpath.Type: GrantFiled: March 15, 2013Date of Patent: December 27, 2016Assignee: General Electric CompanyInventors: Kaitlin Marie Graham, Krishna Kumar Venkataraman, Lewis Berkley Davis, Jr.
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Patent number: 9482434Abstract: A method for use in a gas turbine engine. The method includes the steps of: configuring a downstream injection system within the interior flowpath that includes two injection stages, a first stage and a second stage, wherein the first stage and the second stage are each axially spaced from the other; and circumferentially positioning the injectors of the first stage and the second stage based on: a) a characteristic of an anticipated combustion flow occurring just upstream of the first stage during a mode of operation; and b) the characteristic of an anticipated combustion flow just downstream of the second stage given an anticipated effect of the air and fuel injection from the first stage and the second stage.Type: GrantFiled: March 15, 2013Date of Patent: November 1, 2016Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Kaitlin Marie Graham
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Patent number: 9435541Abstract: A gas turbine that includes: a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a primary air and fuel injection system that defines a forward end, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end; and a downstream injection system that includes two injection stages, a first stage and a second stage, that are axially spaced along the longitudinal axis of the interior flowpath. The first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath.Type: GrantFiled: March 15, 2013Date of Patent: September 6, 2016Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Kaitlin Marie Graham
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Publication number: 20140260303Abstract: A method for use in a gas turbine engine. The method includes the steps of: configuring a downstream injection system within the interior flowpath that includes two injection stages, a first stage and a second stage, wherein the first stage and the second stage are each axially spaced from the other; and circumferentially positioning the injectors of the first stage and the second stage based on: a) a characteristic of an anticipated combustion flow occurring just upstream of the first stage during a mode of operation; and b) the characteristic of an anticipated combustion flow just downstream of the second stage given an anticipated effect of the air and fuel injection from the first stage and the second stage.Type: ApplicationFiled: March 15, 2013Publication date: September 18, 2014Inventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Kaitlin Marie Graham
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Publication number: 20140260262Abstract: A gas turbine that includes: a combustor coupled to a turbine that together define an interior flowpath, the interior flowpath extending aftward about a longitudinal axis from a primary air and fuel injection system that defines a forward end, through an interface at which the combustor connects to the turbine, and through a row of stator blades in the turbine that defines an aft end; and a downstream injection system that includes two injection stages, a first stage and a second stage, that are axially spaced along the longitudinal axis of the interior flowpath. The first stage and the second stage each includes multiple injectors configured to inject an air and fuel mixture into the interior flowpath.Type: ApplicationFiled: March 15, 2013Publication date: September 18, 2014Inventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Kaitlin Marie Graham
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Patent number: 8707704Abstract: A method of assembling a turbine engine includes defining a first chamber and defining a second chamber. The method also includes forming at least one venturi device oriented with a predetermined venturi step angle greater than approximately 48°. The method further includes coupling the first chamber in flow communication with the second chamber via the venturi device therebetween.Type: GrantFiled: May 31, 2007Date of Patent: April 29, 2014Assignee: General Electric CompanyInventors: Derrick Walter Simons, Jeffrey Scott Lebegue, Krishna Kumar Venkataraman
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Patent number: 8707707Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto is combustible, a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power a rotation of the turbine blades, a transition zone, including a second interior in which a second fuel supplied thereto and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are supported by the transition zone and coupled to a fuel circuit, and which are configured to supply the second fuel to the second interior in any one or more of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 29, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Jason Charles Terry, Chetan Babu Velkur, Hasan Karim
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Patent number: 8701382Abstract: A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Jason Charles Terry
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Patent number: 8701418Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, the first fuel including natural gas and/or a blend of natural gas and alternate gas receivable by a fuel circuit from an external source, a turbine, a transition zone, including a second interior in which a second fuel, the second fuel including an unblended supply of the alternate gas receivable by the fuel circuit from the external source, and the products of the combustion of the first fuel are combustible, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Jason Charles Terry
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Patent number: 8701383Abstract: A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Roy Marshall Washam, Hasan Karim, Jason Charles Terry, Lewis Berkley Davis, Jr.
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Patent number: 8683808Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, and a control system coupled to the fuel circuit and configured to control relative amounts of the first and second fuels supplied by the fuel circuit to the first and second interiors.Type: GrantFiled: January 7, 2009Date of Patent: April 1, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Lewis Berkley Davis, Jr.
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Patent number: 8457861Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: GrantFiled: August 24, 2012Date of Patent: June 4, 2013Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20130111918Abstract: A turbomachine combustor assembly includes a combustor housing, a first combustion zone arranged in the combustor housing, a second combustion zone arranged downstream from the first combustion zone, and one or more injector assemblies positioned downstream from the first combustion zone and upstream from the second combustion zone. The one or more injector assemblies includes a first injector member having a first centerline axis and a second injector member having a second centerline axis. The second injector member extends though the first injector member with the second centerline axis being off-set from the first centerline axis.Type: ApplicationFiled: November 7, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Atanu Kumar Kundu, Karim Hasan, Arjun Singh, Krishna Kumar Venkataraman
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Patent number: 8381526Abstract: A combustor includes a first flow path and a second flow path. The first flow path places a diffuser in indirect fluid communication with a combustor cap assembly by way of an intervening lower combustor annular passageway. The second flow path places the diffuser in direct fluid communication with the combustor cap assembly.Type: GrantFiled: February 15, 2010Date of Patent: February 26, 2013Assignee: General Electric CompanyInventors: Jonathan Dwight Berry, Constantin Dinu, Carl Robert Barker, Krishna Kumar Venkataraman
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Publication number: 20130036743Abstract: A combustor assembly includes a combustor body having a combustion chamber, and a nozzle support mounted to the combustor body. The nozzle support includes a central opening, and a plurality of openings extending about the central opening. A central flame tolerant nozzle assembly is positioned within the central opening, and a plurality of micro-mixer nozzle assemblies are mounted in respective ones of the plurality of openings about the central flame tolerant nozzle assembly. Each of the central flame tolerant nozzle assembly and the plurality of micro-mixer nozzle assemblies are configured and disposed to deliver an air-fuel mixture into the combustion chamber.Type: ApplicationFiled: August 8, 2011Publication date: February 14, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Abdul Rafey Khan, Krishna Kumar Venkataraman
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Publication number: 20120312024Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: ApplicationFiled: August 24, 2012Publication date: December 13, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Patent number: 8275533Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: GrantFiled: January 6, 2012Date of Patent: September 25, 2012Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20120110974Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: ApplicationFiled: January 6, 2012Publication date: May 10, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Patent number: 8156743Abstract: Disclosed is an arrangement for expanding an annular fluid flow and a center fluid flow, comprising a combustor including a venturi and a centerbody, the centerbody including an upstream end and a downstream end, and a venturi throat defined by the venturi and disposed upstream of 0.19 inches downstream of the downstream end of the centerbody.Type: GrantFiled: May 4, 2006Date of Patent: April 17, 2012Assignee: General Electric CompanyInventors: William Kirk Hessler, Alberto Jose Negroni, Predrag Popovic, Krishna Kumar Venkataraman