Patents by Inventor Shivakumar Srinivasan
Shivakumar Srinivasan 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: 10054314Abstract: An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which compressed air flows from a compressed air source to a transition duct of a gas turbine combustor. The body includes a plurality of outlets disposed on an interior surface thereof. Each outlet of the plurality of outlets includes a secondary fuel conduit in fluid communication with a secondary fuel source, and includes a first wall that defines a secondary fuel path. The secondary compressed air conduit is in fluid communication with a compressed air source, and includes a second wall disposed about the first wall in a substantially coannular arrangement, wherein the first wall and the second wall define a secondary compressed air flow path.Type: GrantFiled: December 17, 2015Date of Patent: August 21, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Sravan Kumar Dheeraj Kapilavai, Wei Zhao, Shivakumar Srinivasan
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Publication number: 20170176015Abstract: An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which compressed air flows from a compressed air source to a transition duct of a gas turbine combustor. The body includes a plurality of outlets disposed on an interior surface thereof. Each outlet of the plurality of outlets includes a secondary fuel conduit in fluid communication with a secondary fuel source, and includes a first wall that defines a secondary fuel path. The secondary compressed air conduit is in fluid communication with a compressed air source, and includes a second wall disposed about the first wall in a substantially coannular arrangement, wherein the first wall and the second wall define a secondary compressed air flow path.Type: ApplicationFiled: December 17, 2015Publication date: June 22, 2017Inventors: Sravan Kumar Dheeraj Kapilavai, Wei Zhao, Shivakumar Srinivasan
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Patent number: 8904802Abstract: A turbomachine combustor assembly includes a combustor body, and a combustor liner arranged within the combustor body and defining a combustion chamber. The combustor liner includes a venturi portion arranged within the combustion chamber. A fluid passage is defined between the combustor body and the combustor liner, and at least one turbulator is arranged in the fluid passage. The at least one turbulator is configured and disposed to create vortices in the fluid passage. A vortex modification system is arranged at the fluid passage and is configured and disposed to disrupt the vortices in the fluid passage.Type: GrantFiled: June 30, 2011Date of Patent: December 9, 2014Assignee: General Electric CompanyInventors: Sridhar Venkat Kodukulla, Ronald James Chila, Sarah Lori Crothers, Shreekrishna Jayakumar Rao, Shivakumar Srinivasan
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Patent number: 8875516Abstract: A turbomachine combustor includes a combustion chamber; a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, wherein fuel from the supply pipe mixes with air in the nozzle body prior to discharge into the combustion chamber; and wherein at least some of the nozzle bodies of the plurality of micro-mixer nozzles have axial length dimensions that differ from axial length dimensions of other of the nozzle bodies.Type: GrantFiled: February 4, 2011Date of Patent: November 4, 2014Assignee: General Electric CompanyInventors: Jong Ho Uhm, Baifang Zuo, William David York, Shivakumar Srinivasan
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Publication number: 20130000312Abstract: A turbomachine combustor assembly includes a combustor body, and a combustor liner arranged within the combustor body and defining a combustion chamber. The combustor liner includes a venturi portion arranged within the combustion chamber. A fluid passage is defined between the combustor body and the combustor liner, and at least one turbulator is arranged in the fluid passage. The at least one turbulator is configured and disposed to create vortices in the fluid passage. A vortex modification system is arranged at the fluid passage and is configured and disposed to disrupt the vortices in the fluid passage.Type: ApplicationFiled: June 30, 2011Publication date: January 3, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Sridhar Venkat Kodukulla, Ronald James Chila, Sarah Lori Crothers, Shreekrishna Jayakumar Rao, Shivakumar Srinivasan
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Publication number: 20130006581Abstract: A system and method each utilize combustion dynamics data to monitor and assess gas turbine combustor health and performance. The system and method each employ a physics-based model to differentiate changes in the spectral features attributable to variations in the operating conditions from differences caused from changes in the hardware.Type: ApplicationFiled: June 30, 2011Publication date: January 3, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Kapil Kumar Singh, Fei Han, Deepali Nitin Bhate, Shivakumar Srinivasan, Preetham Balasubramanyam, Qingguo Zhang, KrishnaKumar Venkatesan, Christian Lee Vandervort
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Publication number: 20120198856Abstract: A turbomachine combustor includes a combustion chamber; a plurality of micro-mixer nozzles mounted to an end cover of the combustion chamber, each including a fuel supply pipe affixed to a nozzle body located within the combustion chamber, wherein fuel from the supply pipe mixes with air in the nozzle body prior to discharge into the combustion chamber; and wherein at least some of the nozzle bodies of the plurality of micro-mixer nozzles have axial length dimensions that differ from axial length dimensions of other of the nozzle bodies.Type: ApplicationFiled: February 4, 2011Publication date: August 9, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Jong Ho UHM, Baifang ZUO, William David YORK, Shivakumar SRINIVASAN
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Patent number: 8061118Abstract: A method for adjusting fuel flow to individual combustion chambers in a gas turbine having fuel nozzles for each combustion chamber, manifolds for supplying fuel to at least one fuel nozzle in each combustion chamber, wherein the manifolds have flow metering devices for the fuel nozzles and a controller for adjusting the flow metering devices, the method including: supplying fuel to the combustion chambers through at least one of the manifolds; combusting the fuel in the combustion chambers and generating exhaust gases which drive the gas turbine; determining whether one of the combustion chambers is operating relatively lean or rich by actuating a corresponding to the one of the combustion chambers to adjust fuel flowing to the one of the combustion chambers; sensing a condition of the exhaust gases at various exhaust regions in the exhaust gases and determining a change in the condition of the exhaust gas due to the actuation of the flow metering device, and correlating the change in the sensed condition ofType: GrantFiled: September 14, 2007Date of Patent: November 22, 2011Assignee: General Electric CompanyInventors: Vasanth Srinivasa Kothnur, Shivakumar Srinivasan
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Publication number: 20100192578Abstract: A system for suppressing combustion instability in a turbomachine includes at least one combustion chamber operatively connected to the turbomachine, and at least one pre-mixer mounted to the at least one combustion chamber. The at least one pre-mixer is configured to receive an amount of fuel and an amount of air that is combined and discharged into the at least one combustion chamber. In addition, the turbomachine includes a combustion instability suppression system operatively associated with the at least one pre-mixer. The combustion instability suppression system is configured to create a combustion asymmetry. The combustion asymmetry facilitates combustion instability suppression in the turbomachine.Type: ApplicationFiled: January 30, 2009Publication date: August 5, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Kapil Kumar Singh, Fei Han, Keith Robert McManus, Shivakumar Srinivasan, Kwanwoo Kim
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Patent number: 7441411Abstract: A method for determining when a combustor is experiencing hardware damage includes sensing acoustic vibrations of a plurality of combustor cans, determining a center frequency for each acoustic tone of the sensed acoustic vibrations within a predetermined frequency range, and indicating an alarm when a center frequency of one or more of the combustor cans changes in a different manner compared to a representative center frequency of the plurality of combustor cans.Type: GrantFiled: September 16, 2005Date of Patent: October 28, 2008Assignee: General Electric CompanyInventors: Eamon Patrick Gleeson, Warren James Mick, George Edward Williams, Fei Han, Shivakumar Srinivasan, Scott Alan Kopcho, Ilan Leibu
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Publication number: 20080000214Abstract: A method for adjusting fuel flow to individual combustion chambers in a gas turbine having fuel nozzles for each combustion chamber, manifolds for supplying fuel to at least one fuel nozzle in each combustion chamber, wherein the manifolds have flow metering devices for the fuel nozzles and a controller for adjusting the flow metering devices, the method including: supplying fuel to the combustion chambers through at least one of the manifolds; combusting the fuel in the combustion chambers and generating exhaust gases which drive the gas turbine; determining whether one of the combustion chambers is operating relatively lean or rich by actuating a corresponding to the one of the combustion chambers to adjust fuel flowing to the one of the combustion chambers; sensing a condition of the exhaust gases at various exhaust regions in the exhaust gases and determining a change in the condition of the exhaust gas due to the actuation of the flow metering device, and correlating the change in the sensed condition ofType: ApplicationFiled: September 14, 2007Publication date: January 3, 2008Applicant: GENERAL ELECTRIC COMPANYInventors: Vasanth Kothnur, Shivakumar Srinivasan
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Patent number: 7269939Abstract: A gas turbine combustion system having: a plurality of combustion chambers; a plurality of fuel nozzles for each of combustion chamber; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers; each of the manifolds having fuel trim control valves for the fuel nozzles, wherein the fuel trim control valves are mounted on the multiple manifolds for metering the fuel to the fuel nozzles in the combustion chambers, and a trim valve controller automatically actuates one or more of the fuel trim valves to adjust fuel to the fuel nozzles based on gas turbine operating conditions.Type: GrantFiled: November 24, 2004Date of Patent: September 18, 2007Assignee: General Electric CompanyInventors: Vasanth Srinivasa Kothnur, Shivakumar Srinivasan
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Publication number: 20070062196Abstract: A method for determining when a combustor is experiencing hardware damage includes sensing acoustic vibrations of a plurality of combustor cans, determining a center frequency for each acoustic tone of the sensed acoustic vibrations within a predetermined frequency range, and indicating an alarm when a center frequency of one or more of the combustor cans changes in a different manner compared to a representative center frequency of the plurality of combustor cans.Type: ApplicationFiled: September 16, 2005Publication date: March 22, 2007Inventors: Eamon Gleeson, Warren Mick, George Williams, Fei Han, Shivakumar Srinivasan, Scott Kopcho, Ilan Leibu
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Publication number: 20060107666Abstract: A gas turbine combustion system having: a plurality of combustion chambers; a plurality of fuel nozzles for each of combustion chamber; a plurality of manifolds for supplying fuel to at least one fuel nozzle in each of the combustion chambers; each of the manifolds having fuel trim control valves for the fuel nozzles, wherein the fuel trim control valves are mounted on the multiple manifolds for metering the fuel to the fuel nozzles in the combustion chambers, and a trim valve controller automatically actuates one or more of the fuel trim valves to adjust fuel to the fuel nozzles based on gas turbine operating conditions.Type: ApplicationFiled: November 24, 2004Publication date: May 25, 2006Applicant: General Electric CompanyInventors: Vasanth Kothnur, Shivakumar Srinivasan