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: 8141879Abstract: A side seal for sealing the side edges of adjacent combustors of a turbine engine include extended ends. The extended ends of the side seal abut and seal against inner and outer circumferential seals to prevent leakage of combustion gases.Type: GrantFiled: July 20, 2009Date of Patent: March 27, 2012Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Kevin Weston McMahan, Timur R. Repikov, Kara Edwards
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Publication number: 20120031097Abstract: The present application provides a fuel nozzle for use in a gas turbine. The fuel nozzle may include a mounting flange, a number of premixers attached to each other, and a number of gas pathways extending from the mounting flange to the number of premixers.Type: ApplicationFiled: May 7, 2009Publication date: February 9, 2012Applicant: General Electric CompanyInventors: Kevin Weston McMahan, Krishna Kumar Venkataraman, Jonathan Dwight Berry, Sergey Aleksandrovich Stryapuninr
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Patent number: 8112216Abstract: 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 7, 2009Date of Patent: February 7, 2012Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20110247340Abstract: A combustion liner assembly for a gas turbine includes an outer liner, the outer liner having a flange at a forward end. An inner liner is disposed within the outer liner. The inner liner has a first inner wall. A venturi includes a second inner wall, a venturi throat, and the first inner wall of the inner liner. A slip joint is connected to the second inner wall. The slip joint receives the flange of the outer liner. Alternatively, or additionally, the combustion liner assembly includes a slip joint between the inner or outer liner and an aft section.Type: ApplicationFiled: April 13, 2010Publication date: October 13, 2011Inventors: Predrag POPOVIC, Krishna Kumar Venkataraman, Derrick Walter Simons, Ajay Kumar Gupta, William Kirk Hessler, Jeffrey Lebegue
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Patent number: 8020385Abstract: A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage defined by a gap between the wall of the centerbody and the external turbulator. The external turbulator member includes a step positioned at the second end of the centerbody. The step defines a radial distance about the second end of the centerbody. The external turbulator member is formed having a step-to-gap ratio relative to the centerbody in a range of about 0.8 to about 1.2.Type: GrantFiled: July 28, 2008Date of Patent: September 20, 2011Assignee: General Electric CompanyInventors: Predrag Popovic, William Kirk Hessler, Krishna Kumar Venkataraman
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Patent number: 8019523Abstract: 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 7, 2009Date of Patent: September 13, 2011Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20110197586Abstract: 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: ApplicationFiled: February 15, 2010Publication date: August 18, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Jonathan Dwight Berry, Constantin Dinu, Carl Robert Barker, Krishna Kumar Venkataraman
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Publication number: 20110072826Abstract: In exemplary embodiments, a gas turbine system is provided. The gas turbine system can include a compressor configured to compress air and combustor cans in flow communication with the compressor, the combustor cans being configured to receive compressed air from the compressor and to combust a fuel stream. The gas turbine system can also include a multi-circuit manifold coupled to the combustor cans and configured to provide a split fuel stream from the fuel stream to the combustor cans.Type: ApplicationFiled: September 25, 2009Publication date: March 31, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Venkateswarlu Narra, Lewis Berkley Davis, Jr., Fei Han, Kwanwoo Kim, Kapil Kumar Singh, Shiva Kumar Srinivasan, Krishna Kumar Venkataraman
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Patent number: 7887322Abstract: Disclosed is a mixing hole arrangement for improving homogeneity of an air and fuel mixture in a combustor, the mixing hole arrangement comprising a plurality of mixing holes defined by a liner, wherein at least one of the plurality of mixing holes is a mixing hole that is at least one of sized and positioned to impede penetration of a fluid flow into a primary mixing zone located in a head end of the combustor.Type: GrantFiled: September 12, 2006Date of Patent: February 15, 2011Assignee: General Electric CompanyInventors: Predrag Popovic, Derrick Walter Simons, Krishna Kumar Venkataraman
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Publication number: 20110014029Abstract: A side seal for sealing the side edges of adjacent combustors of a turbine engine include extended ends. The extended ends of the side seal abut and seal against inner and outer circumferential seals to prevent leakage of combustion gases.Type: ApplicationFiled: July 20, 2009Publication date: January 20, 2011Inventors: Krishna Kumar VENKATARAMAN, Kevin Weston MCMAHAN, Timur R. REPIKOV, Kara EDWARDS
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Publication number: 20100170219Abstract: 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: ApplicationFiled: January 7, 2009Publication date: July 8, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Krishna Kumar Venkataraman, Lewis Berkley Davis, JR.
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Publication number: 20100170252Abstract: 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: ApplicationFiled: January 7, 2009Publication date: July 8, 2010Applicant: General Electric CompanyInventors: Krishna Kumar Venkataraman, Jason Charles Terry
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Publication number: 20100170251Abstract: 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: ApplicationFiled: January 7, 2009Publication date: July 8, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Jason Charles Terry
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Publication number: 20100174466Abstract: 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 7, 2009Publication date: July 8, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20100170216Abstract: 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: ApplicationFiled: January 7, 2009Publication date: July 8, 2010Applicant: General Electric CompanyInventors: Krishna Kumar Venkataraman, Roy Marshall Washam, Hasan Karim, Jason Charles Terry, Lewis Berkley Davis, JR.
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Publication number: 20100170254Abstract: 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: ApplicationFiled: January 7, 2009Publication date: July 8, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Krishna Kumar Venkataraman, Jason Charles Terry, Chetan Babu Velkur, Hasan Karim
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Publication number: 20100018181Abstract: A turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a centerbody within the cap assembly, a wall of the centerbody having a first end, a second end and an intermediate portion, and an external turbulator member in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage defined by a gap between the wall of the centerbody and the external turbulator. The external turbulator member includes a step positioned at the second end of the centerbody. The step defines a radial distance about the second end of the centerbody. The external turbulator member is formed having a step-to-gap ratio relative to the centerbody in a range of about 0.8 to about 1.2.Type: ApplicationFiled: July 28, 2008Publication date: January 28, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Predrag Popovic, William Kirk Hessler, Krishna Kumar Venkataraman
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Publication number: 20080295521Abstract: 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: ApplicationFiled: May 31, 2007Publication date: December 4, 2008Inventors: Derrick Walter Simons, Jeffrey Scott Lebegue, Krishna Kumar Venkataraman
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Publication number: 20080060358Abstract: Disclosed is a mixing hole arrangement for improving homogeneity of an air and fuel mixture in a combustor, the mixing hole arrangement comprising a plurality of mixing holes defined by a liner, wherein at least one of the plurality of mixing holes is a mixing hole that is at least one of sized and positioned to impede penetration of a fluid flow into a primary mixing zone located in a head end of the combustor.Type: ApplicationFiled: September 12, 2006Publication date: March 13, 2008Applicant: GENERAL ELECTRIC COMPANYInventors: Predrag Popovic, Derrick Walter Simons, Krishna Kumar Venkataraman
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Patent number: 7093438Abstract: A gas fuel injector includes a first header plate; a second header plate spaced downstream from the upstream header plate; and a plurality of venturi tubes arranged in rows and sealably secured to the first and second header plates. Each of the venturi tubes includes an inlet section, a throat section and an exit. The exit is shaped into a pattern that reduces space between each of the venturi tubes at the exit of each of the plurality of venturi tubes.Type: GrantFiled: January 17, 2005Date of Patent: August 22, 2006Assignee: General Electric CompanyInventors: Constantin Dinu, Thomas Raymond Farrell, Kevin M. Gordon, James Michael Storey, Krishna Kumar Venkataraman