Patents by Inventor Predrag Popovic
Predrag Popovic 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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Publication number: 20170184310Abstract: A system for injecting a liquid fuel into a combustion gas flow field includes an annular liner that defines a combustion gas flow path. The annular liner includes an inner wall, an outer wall and a fuel injector opening that extends through the inner wall and the outer wall. The system further includes a gas fuel injector that is coaxially aligned with the fuel injector opening. The gas fuel injector includes an upstream end and a downstream end. The downstream end terminates substantially adjacent to the inner wall. A dilution air passage is at least partially defined by the gas fuel injector. A liquid fuel injector extends partially through the dilution air passage. The liquid fuel injector includes an injection end that terminates upstream from the inner wall.Type: ApplicationFiled: March 14, 2017Publication date: June 29, 2017Inventors: Abinash Baruah, Gilbert Otto Kraemer, Predrag Popovic, William Francis Carnell, JR.
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Patent number: 9500369Abstract: A fuel nozzle and a method for operating a combustor are disclosed. The method includes flowing a fuel and an oxidizer through a fuel nozzle, the fuel nozzle comprising an inner tube, an intermediate tube, and an outer tube each configured for flowing one of the fuel or the oxidizer therethrough. At least one of the inner tube, the intermediate tube, or the outer tube includes a plurality of swirler vanes. The method further includes imparting a swirl to the fuel and the oxidizer in the fuel nozzle, and exhausting the fuel and the oxidizer from the fuel nozzle into a combustion zone.Type: GrantFiled: April 18, 2012Date of Patent: November 22, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Predrag Popovic, Gilbert Otto Kraemer, William Thomas Ross, Vladimir Belvaev
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Patent number: 9382850Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured operating parameter of the combustor.Type: GrantFiled: March 21, 2013Date of Patent: July 5, 2016Assignee: General Electric CompanyInventors: Arvind Venugopal Menon, Alan Meier Truesdale, Abhijit Prabhakar Kulkarni, Predrag Popovic
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Patent number: 9377202Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel.Type: GrantFiled: March 15, 2013Date of Patent: June 28, 2016Assignee: General Electric CompanyInventors: Arvind Venugopal Menon, Alan Meier Truesdale, Abhijit Prabhakar Kulkarni, Predrag Popovic
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Patent number: 9347376Abstract: A system for supplying a gaseous fuel to a gas turbine includes a liquefied fuel source for supplying a liquefied fuel to a liquid fuel pump that is disposed downstream from the liquefied fuel source. The liquid fuel pump is sufficient to raise the pressure of the liquefied fuel to a substantially supercritical pressure. A supercritical liquefied fuel vaporizer is disposed downstream from the liquid fuel pump. A heat recovery system is in thermal communication with the liquefied fuel. The heat recovery system is positioned between the liquid fuel source and the supercritical liquefied fuel vaporizer.Type: GrantFiled: April 24, 2013Date of Patent: May 24, 2016Assignee: GENERAL ELECTRIC COMPANYInventor: Predrag Popovic
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Patent number: 9297315Abstract: Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment.Type: GrantFiled: September 28, 2012Date of Patent: March 29, 2016Assignee: General Electric CompanyInventors: Derrick Simons, Douglas Dean, Carey Romoser, Kevin Wilkes, Predrag Popovic, Abhijit Kulkarni
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Publication number: 20160068777Abstract: A system, method, and computer-readable medium for blending a fuel for use in a gas turbine are disclosed. A measurement of a heating value of a process gas and a measurement of a molecular weight of the process gas is obtained. An estimate of a composition of the process gas is obtained using the obtained measurement of the heating value and the obtained measurement of the molecular weight. A blending ratio of the process gas and a natural gas is selected based on the estimate of the composition of the process gas. The process gas and the natural gas are then blended according to the selected blending ratio to obtain a fuel mixture for use in the gas turbine.Type: ApplicationFiled: September 5, 2014Publication date: March 10, 2016Inventors: Arvind Venugopal Menon, Abhijit Prabhakar Kulkarni, Predrag Popovic, Alan Meier Truesdale
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Patent number: 9181876Abstract: A gas turbine includes a compressor, a combustor downstream from the compressor and a heat transfer system, wherein the heat transfer system receives a compressed working fluid from the compressor. A fluid coupling between the heat transfer system and the combustor, wherein the fluid coupling receives the compressed working fluid from the heat transfer system. A conditioner in fluid communication with the compressor and a fluid coupling between the heat transfer system and the conditioner, wherein the fluid coupling receives a cooling media from the heat transfer system. A method for operating the gas turbine includes flowing a compressed working fluid from the compressor to the heat transfer system, transferring heat energy from the compressed working fluid to the heat transfer system, flowing the compressed working fluid from the heat transfer system to a combustor, and flowing a cooling media from the heat transfer system to a compressor inlet.Type: GrantFiled: January 4, 2012Date of Patent: November 10, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Predrag Popovic, William Francis Carnell, Jr., Andrew Mitchell Rodwell
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Publication number: 20150135723Abstract: A combustor nozzle includes a fuel passage that extends generally axially in the nozzle and a surface that extends radially across at least a portion of the fuel passage. A projection in the surface extends generally axially down-stream from the surface, and an indention in the surface radially surrounds the projection. An oxidant supply is in fluid communication with an oxidant passage, and the oxidant passage is radially displaced from the fuel passage and terminates at an oxidant outlet. A method of supplying a fuel to a combustor includes flowing fuel through a projection in a surface, wherein the projection extends generally axially downstream from the surface, and flowing fuel through an indention in the surface, wherein the indention radially surrounds the projection. The method further includes flowing an oxidant through an oxidant outlet that circumferentially surrounds the indention in the surface.Type: ApplicationFiled: February 21, 2012Publication date: May 21, 2015Applicant: General Electric CompanyInventors: Vladimir Vasilyevich Belyaev, Gilber Otto Kraemer, Predrag Popovic
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Publication number: 20150047360Abstract: A system for injecting a liquid fuel into a combustion gas flow field includes an annular liner that defines a combustion gas flow path. The annular liner includes an inner wall, an outer wall and a fuel injector opening that extends through the inner wall and the outer wall. The system further includes a gas fuel injector that is coaxially aligned with the fuel injector opening. The gas fuel injector includes an upstream end and a downstream end. The downstream end terminates substantially adjacent to the inner wall. A dilution air passage is at least partially defined by the gas fuel injector. A liquid fuel injector extends partially through the dilution air passage. The liquid fuel injector includes an injection end that terminates upstream from the inner wall.Type: ApplicationFiled: August 13, 2013Publication date: February 19, 2015Applicant: General Electric CompanyInventors: Abinash Baruah, Gilbert Otto Kraemer, Predrag Popovic, William Francis Carnell, JR.
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Patent number: 8955329Abstract: A fuel nozzle assembly has been conceived for a combustor in a gas turbine including a first passage and fourth passage connectable to a source of gaseous fuel, a second passage connectable to a source of a gaseous oxidizer, and a third passage coupled to a source of a diluent gas, wherein the first passage is a center passage and is configured to discharge gaseous fuel from nozzles at a discharge end of the center passage, the second passage is configured to discharge the gaseous oxidizer through nozzles adjacent to the nozzles for the center passage, the third passage discharges a diluent gas through nozzles adjacent to the nozzles for the second passage, and the fourth passage is configured to discharges the gaseous fuel downstream of the discharge location for the first, second and third passages.Type: GrantFiled: October 21, 2011Date of Patent: February 17, 2015Assignee: General Electric CompanyInventors: Predrag Popovic, Abinash Baruah
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Publication number: 20140318134Abstract: A system for supplying a gaseous fuel to a gas turbine includes a liquefied fuel source for supplying a liquefied fuel to a liquid fuel pump that is disposed downstream from the liquefied fuel source. The liquid fuel pump is sufficient to raise the pressure of the liquefied fuel to a substantially supercritical pressure. A supercritical liquefied fuel vaporizer is disposed downstream from the liquid fuel pump. A heat recovery system is in thermal communication with the liquefied fuel. The heat recovery system is positioned between the liquid fuel source and the supercritical liquefied fuel vaporizer.Type: ApplicationFiled: April 24, 2013Publication date: October 30, 2014Applicant: General Electric CompanyInventor: Predrag Popovic
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Publication number: 20140283523Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured operating parameter of the combustor.Type: ApplicationFiled: March 21, 2013Publication date: September 25, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Arvind Venugopal Menon, Alan Meier Truesdale, Abhijit Prabhakar Kulkarni, Predrag Popovic
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Publication number: 20140260309Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel.Type: ApplicationFiled: March 15, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Arvind Venugopal Menon, Alan Meier Truesdale, Abhijit Prabhakar Kulkarni, Predrag Popovic
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Publication number: 20140260302Abstract: The present application and the resultant patent provide a diffusion combustor fuel nozzle for a gas turbine engine. The fuel nozzle may include one or more gas fuel passages for one or more flows of gas fuel, a swirler surrounding the one or more gas fuel passages and positioned about a downstream face of the fuel nozzle, a number of swirler gas fuel ports defined in the swirler, and a number of downstream face gas fuel ports defined in the downstream face of the fuel nozzle. The swirler may include a number of swirl vanes and a number of air chambers defined between adjacent swirl vanes. The present application and the resultant patent further provide a method of operating a diffusion combustor fuel nozzle of a gas turbine engine.Type: ApplicationFiled: March 14, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Arvind Venugopal Menon, Gilbert Otto Kraemer, Predrag Popovic, Abinash Baruah
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Publication number: 20140090353Abstract: Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment.Type: ApplicationFiled: September 28, 2012Publication date: April 3, 2014Applicant: General Electric CompanyInventors: Derrick Simons, Douglas Dean, Carey Romoser, Kevin Wilkes, Predrag Popovic, Abhijit Kulkarni
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Publication number: 20130276450Abstract: Gas turbine combustor with a specific fuel and oxidizer flow arrangement which provides high combustion efficiency for stoichiometric diffusion combustion in gas turbine applications operating with oxygen deficient working fluids.Type: ApplicationFiled: April 24, 2012Publication date: October 24, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Abinash BARUAH, Gilbert Otto KRAEMER, Predrag POPOVIC, Hasan Ul KARIM
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Publication number: 20130263605Abstract: The present application thus provides a fuel nozzle for use with one or more flows of fuel and a flow of air in a combustor. The fuel nozzle may include one or more gas fuel passages for the one or more of flows of fuel, a swirler with one or more air chambers therein surrounding the gas fuel passages, and a collar with one or more curtain slots surrounding the swirler. The flow of air is divided between a swirler flow through the air chambers and a curtain flow through the curtain slots.Type: ApplicationFiled: April 4, 2012Publication date: October 10, 2013Applicant: GENERAL ELECTRICInventors: Abinash Baruah, Gilbert Otto Kraemer, Predrag Popovic, Arvind Venugopal Menon
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Patent number: 8522554Abstract: A secondary fuel nozzle for a turbine includes a passive purge air passageway which provides purge air to the secondary nozzle at all times that the nozzle is in operation. The passive purge air passageway draws in air from a location adjacent an upstream end of the nozzle. Because of a pressure differential between air located at the downstream end of the nozzle and air located at the upstream end of the nozzle, purge air will run through the passive purge air passageway at all times the nozzle is in operation. There is no need for a supply of compressed purge air.Type: GrantFiled: January 5, 2010Date of Patent: September 3, 2013Assignee: General Electric CompanyInventors: John Intile, Predrag Popovic, Lucas John Stoia
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Publication number: 20130167548Abstract: A gas turbine includes a compressor, a combustor downstream from the compressor and a heat transfer system, wherein the heat transfer system receives a compressed working fluid from the compressor. A fluid coupling between the heat transfer system and the combustor, wherein the fluid coupling receives the compressed working fluid from the heat transfer system. A conditioner in fluid communication with the compressor and a fluid coupling between the heat transfer system and the conditioner, wherein the fluid coupling receives a cooling media from the heat transfer system. A method for operating the gas turbine includes flowing a compressed working fluid from the compressor to the heat transfer system, transferring heat energy from the compressed working fluid to the heat transfer system, flowing the compressed working fluid from the heat transfer system to a combustor, and flowing a cooling media from the heat transfer system to a compressor inlet.Type: ApplicationFiled: January 4, 2012Publication date: July 4, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Predrag Popovic, William Francis Carnell, JR., Andrew Mitchell Rodwell