Patents by Inventor Krishnakumar Venkatesan
Krishnakumar Venkatesan 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: 11906165Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.Type: GrantFiled: April 11, 2022Date of Patent: February 20, 2024Assignee: General Electric CompanyInventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
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Patent number: 11795879Abstract: A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.Type: GrantFiled: January 31, 2022Date of Patent: October 24, 2023Assignee: General Electric CompanyInventors: Krishnakumar Venkatesan, Michael A. Benjamin, Michael T. Bucaro
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Publication number: 20230323809Abstract: A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.Type: ApplicationFiled: April 12, 2022Publication date: October 12, 2023Inventors: Arin Elspeth Lastufka Cross, Krishnakumar Venkatesan
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Publication number: 20230194090Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a combustion chamber, a compressed air passage fluidly coupled to the combustion chamber, and a swirler. At least one acoustic resonator can be provided in the combustor.Type: ApplicationFiled: February 16, 2022Publication date: June 22, 2023Inventors: Ramal Janith Samarasinghe, Fei Han, Krishnakumar Venkatesan
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Publication number: 20230194093Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.Type: ApplicationFiled: April 11, 2022Publication date: June 22, 2023Inventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
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Publication number: 20230194094Abstract: A turbine engine having a compressor section, a combustion section and a turbine section in serial flow arrangement. The turbine engine further having a combustor, provided within the combustion section, defining a combustion chamber and having at least one fuel injector. The fuel injector having a fuel channel, a first set of fuel orifices, and a flow restrictor located within the fuel channel and having a second set of fuel orifices.Type: ApplicationFiled: February 22, 2022Publication date: June 22, 2023Inventors: Fei Han, Ramal Janith Samarasinghe, Pradeep Naik, Krishnakumar Venkatesan, Michael T. Bucaro, Ajoy Patra, Manampathy G. Giridharan
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Publication number: 20230193829Abstract: A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.Type: ApplicationFiled: January 31, 2022Publication date: June 22, 2023Inventors: Krishnakumar Venkatesan, Michael A. Benjamin, Michael T. Bucaro
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Patent number: 10352570Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.Type: GrantFiled: March 31, 2016Date of Patent: July 16, 2019Assignee: General Electric CompanyInventors: Krishnakumar Venkatesan, Michael Anthony Benjamin, Shih-Yang Hsieh, Yuxin Zhang, Owen James Sullivan Rickey, Nayan Vinodbhai Patel, Duane Douglas Thomsen, Kevin Vandevoorde
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Publication number: 20190017441Abstract: A gas turbine engine combustor includes a dome plate, an inner liner, and an outer liner. The inner liner and the outer liner are separately coupled to a rear side of the dome plate and both extend rearward therefrom. The outer and inner liners define an annular combustion chamber therebetween that extends rearward from the dome plate. At least one of the outer liner or the dome plate includes an igniter cavity formed therein that is separated from the combustion chamber by a partition wall. The partition wall defines one or more transfer holes therethrough that fluidly connect the igniter cavity to the combustion chamber.Type: ApplicationFiled: July 17, 2017Publication date: January 17, 2019Inventors: Krishnakumar Venkatesan, Narendra Digamber Joshi
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Publication number: 20170284678Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.Type: ApplicationFiled: March 31, 2016Publication date: October 5, 2017Inventors: Krishnakumar Venkatesan, Michael Anthony Benjamin, Shih-Yang Hsieh, Yuxin Zhang, Owen James Sullivan Rickey, Nayan Vinodbhai Patel, Duane Douglas Thomsen, Kevin Vandevoorde
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Publication number: 20160265779Abstract: A fuel nozzle for a gas turbine includes a first radial swirler and a second radial swirler that introduce radial swirl to a flow of pressurized air; a chevron splitter between the two swirlers that directs the swirled flow of pressurized air to a main mixer passage to form a fuel-air mixture with fuel injected into the fuel nozzle; and a main mixer passage that receives the fuel-air mixture from the premixing chamber, and includes a converging throat that accelerates the fuel-air mixture. A method of mixing fuel and air for combustion in a gas turbine includes introducing a radial swirl to first and second flows of pressurized air; directing the swirled, pressurized air to a premixing chamber via a chevron splitter; mixing the swirled, pressurized air with a fuel jet injected into the premixing chamber to form a fuel-air mixture; and accelerating the fuel-air mixture in the main mixer passage having a converging throat.Type: ApplicationFiled: March 11, 2015Publication date: September 15, 2016Inventors: Joel Meier HAYNES, Narendra Digamber JOSHI, David James WALKER, Junwoo LIM, Sarah Marie MONAHAN, Krishnakumar VENKATESAN
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Patent number: 9033259Abstract: A method and system of feeding fuel into a gasifier are provided. The feed injector system includes a first injector port assembly including a plurality of annular channels substantially concentric about a longitudinal axis that define corresponding fluid flow paths that direct a flow of fluid substantially axially therethrough from a respective source to a reaction zone and a second injector port assembly including a flow port surrounded by a plurality of auxiliary ports spaced about a circumference of the flow port, the plurality of auxiliary ports communicatively coupled to a toroidal passage configured to receive a flow of fluid and channel the flow of fluid to the auxiliary ports such that the flow of fluid is discharged from the auxiliary ports having an axial flow component, a radially inward flow component, and a circumferential flow component.Type: GrantFiled: December 23, 2010Date of Patent: May 19, 2015Assignee: General Electric CompanyInventors: Krishnakumar Venkatesan, Ertan Yilmaz, Ali Ergut
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Publication number: 20130160856Abstract: A feed injector system includes an injector nozzle. The injector nozzle includes a first injector port assembly having a first injector port located at a center of a longitudinal axis of the injector nozzle and defining a flow path for directing a first feed flow from a respective source into a reaction zone. The feed injector system also includes a second injector port assembly having one or more second injector passages arranged about a first circumference of the first injector port for receiving and injecting a second feed flow. Further, the feed injector system includes a third injector port assembly having a plurality of third ports arranged about a second circumference of the first injector port. The third ports are communicatively coupled to a plurality of toroidal flow paths and configured to receive and inject a third feed flow.Type: ApplicationFiled: December 22, 2011Publication date: June 27, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Krishnakumar Venkatesan, Ali Ergut, Ertan Yilmaz
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Patent number: 8381525Abstract: A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone.Type: GrantFiled: September 30, 2009Date of Patent: February 26, 2013Assignee: General Electric CompanyInventors: Ahmed Mostafa ELKady, Narendra Digamber Joshi, Parag Prakash Kulkarni, Christian Lee Vandervort, Krishnakumar Venkatesan
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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: 20120160140Abstract: A method and system of feeding fuel into a gasifier are provided. The feed injector system includes a first injector port assembly including a plurality of annular channels substantially concentric about a longitudinal axis that define corresponding fluid flow paths that direct a flow of fluid substantially axially therethrough from a respective source to a reaction zone and a second injector port assembly including a flow port surrounded by a plurality of auxiliary ports spaced about a circumference of the flow port, the plurality of auxiliary ports communicatively coupled to a toroidal passage configured to receive a flow of fluid and channel the flow of fluid to the auxiliary ports such that the flow of fluid is discharged from the auxiliary ports having an axial flow component, a radially inward flow component, and a circumferential flow component.Type: ApplicationFiled: December 23, 2010Publication date: June 28, 2012Inventors: Krishnakumar Venkatesan, Ertan Yilmaz, Ali Ergut
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Publication number: 20110072779Abstract: A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone.Type: ApplicationFiled: September 30, 2009Publication date: March 31, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Ahmed Mostafa ELKady, Narendra Digamber Joshi, Parag Prakash Kulkarni, Christian Lee Vandervort, Krishnakumar Venkatesan