Patents by Inventor Pradeep Naik
Pradeep Naik 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: 12292194Abstract: A combustor for a gas turbine includes a combustor liner, an outer casing surrounding the combustor liner, an ignitor housing extending through an ignitor opening through the liner, and an ignitor disposed within the ignitor housing. The ignitor housing includes a housing wall including at least one airflow inlet passage on a downstream side of the housing wall and arranged within the outer flow passage, and at least one cooling passage on the downstream side within the housing wall. The at least one cooling passage extends along a length of the ignitor housing from the at least one airflow inlet passage and through the inner end of the ignitor housing, the at least one cooling passage being in fluid communication with the at least one airflow inlet passage.Type: GrantFiled: August 30, 2022Date of Patent: May 6, 2025Assignee: GENERAL ELECTIC COMPANYInventors: Karthikeyan Sampath, Perumallu Vukanti, Ajoy Patra, Pradeep Naik, Hiranya Nath
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Patent number: 12287094Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.Type: GrantFiled: July 20, 2023Date of Patent: April 29, 2025Assignee: General Electric CompanyInventors: Perumallu Vukanti, Varun S. Lakshmanan, Michael T. Bucaro, Pradeep Naik, Steven C. Vise, Michael A. Benjamin
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Publication number: 20250129748Abstract: A turbine engine has a combustor in a core air flow path that generates combustion gases and a fuel and steam system fluidly coupled to the combustor. The fuel and steam system has a steam system to provide a steam flow to the combustor and a fuel system to provide a primary fuel flow and a secondary fuel flow to the combustor. The fuel system has a first state in which there is a first flow rate of the secondary fuel flow to the combustor and a second state in which there is a second flow rate of the secondary fuel flow to the combustor. The first flow rate and the second flow rate are different. The first state and the second state are based on a condition of the steam system.Type: ApplicationFiled: October 23, 2023Publication date: April 24, 2025Inventors: Pradeep Naik, Clayton S. Cooper, Steven C. Vise, Michael A. Benjamin, Steven Marakovits, Sibtosh Pal, Sripathi Mohan
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Publication number: 20250129941Abstract: A main mixer for an engine. The main mixer includes a plurality of mixer vanes located circumferentially around a mixer body. Each mixer vane includes a waveform profile. The waveform profile detaches or trips a boundary layer of an air flow across the mixer vane such that the waveform profile introduces turbulence into the air flow.Type: ApplicationFiled: December 30, 2024Publication date: April 24, 2025Inventors: Rimple Rangrej, Saket Singh, Pradeep Naik
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Publication number: 20250129940Abstract: A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.Type: ApplicationFiled: December 20, 2024Publication date: April 24, 2025Inventors: Pradeep Naik, Shai Birmaher, Saket Singh, Krishnendu Chakraborty
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Publication number: 20250123001Abstract: A premixer for a combustor includes: a centerbody having a hollow interior cavity; a swirler assembly radially outward of the centerbody; a peripheral wall disposed radially outward of the centerbody and the swirler assembly such that a mixing duct is defined between the peripheral wall and the centerbody, downstream from the swirler assembly; an annular splitter radially inward of the swirler assembly and radially outward of the centerbody such that a radial gap is defined between the splitter and an outer surface of the centerbody, wherein the splitter includes a trailing edge which extends axially aft of the swirler assembly; a fuel gallery disposed inside the interior cavity of the centerbody; and at least one fuel injector extending outward from the fuel gallery and passing through an injector port communicating with the outer surface of the splitter.Type: ApplicationFiled: December 4, 2024Publication date: April 17, 2025Inventors: Ranjeet Kumar Mishra, Jayanth Sekar, Pradeep Naik, Gregory A. Boardman, Randall C. Boehm
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Patent number: 12276423Abstract: A swirler assembly includes a primary swirler having a primary swirler connecting portion, a fuel nozzle connecting portion for connecting a fuel nozzle to the primary swirler, and a primary oxidizer flow passage that extends at least partially in the longitudinal direction, and a secondary swirler having a secondary swirler connecting member, where the primary swirler connecting portion and the secondary swirler connecting member engage to connect the primary swirler and the secondary swirler in the longitudinal direction, and to permit radial movement of the primary swirler with respect to the secondary swirler.Type: GrantFiled: January 27, 2022Date of Patent: April 15, 2025Assignee: GENERAL ELECTRIC COMPANYInventors: Pradeep Naik, David A. Lind, Shai Birmaher, Ranganatha Narasimha Chiranthan, Ajoy Patra, Saket Singh
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Publication number: 20250116402Abstract: A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.Type: ApplicationFiled: July 10, 2024Publication date: April 10, 2025Inventors: Aritra Chakraborty, Perumallu Vukanti, Pradeep Naik, Arijit Sinha Roy, Bhavya Naidu Panduri, R. Narasimha Chiranthan, Ajoy Patra, Michael T. Bucaro, Sibtosh Pal, Pabitra Badhuk
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Publication number: 20250109853Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section includes a primary combustor liner including an inner liner and an outer liner. A dome wall and a primary dome inlet are located in the dome wall. The outer liner defines at least one opening downstream from the primary dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.Type: ApplicationFiled: September 28, 2023Publication date: April 3, 2025Inventors: Pradeep Naik, Perumallu Vukanti, Ravindra Shankar Ganiger, Sahana Narasimhan Suresh, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Sripathi Mohan, Hiranya Kumar Nath
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Publication number: 20250075910Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.Type: ApplicationFiled: November 19, 2024Publication date: March 6, 2025Inventors: Pradeep Naik, Joseph Zelina, Sripathi Mohan, Perumallu Vukanti, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Karthikeyan Sampath
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Publication number: 20250075911Abstract: A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.Type: ApplicationFiled: November 15, 2024Publication date: March 6, 2025Inventors: Pradeep Naik, Clayton S. Cooper, Perumallu Vukanti, Michael A. Benjamin, Steven C. Vise, Sripathi Mohan
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Patent number: 12241628Abstract: A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.Type: GrantFiled: September 1, 2023Date of Patent: March 4, 2025Assignee: GENERAL ELECTRIC COMPANYInventors: Gurunath Gandikota, Karthikeyan Sampath, Perumallu Vukanti, Allen M. Danis, Scott M. Bush, Steven Clayton Vise, Hari Ravi Chandra, Rimple Rangrej, Saket Singh, Pradeep Naik, Neeraj Kumar Mishra, Arvind Kumar Rao, Balasubramaniam Venkatanarayanan, Ranjeet Kumar Mishra
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Publication number: 20250067214Abstract: A combustor includes a combustion chamber and an annular dome. The combustion chamber includes an outer liner and an inner liner and has a combustion zone. The annular dome is coupled to the outer liner and the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases. A combustor steam system is in fluid communication with the combustion chamber. The combustor steam system includes a steam path defined by at least one of the outer liner, the inner liner, or the annular dome. The combustor steam system operably directs steam through the steam path from the at least one of the outer liner, the inner liner, or the annular dome and into the combustion chamber.Type: ApplicationFiled: November 3, 2023Publication date: February 27, 2025Inventors: Perumallu Vukanti, Pradeep Naik, Saket Singh, Michael A. Benjamin, Sripathi Mohan, Clayton S. Cooper, Rajendra Wankhade, Hiranya Nath, Nicholas R. Overman, Steven C. Vise
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Publication number: 20250067439Abstract: A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone, an annular dome coupled to the outer liner and the inner liner, and a trapped vortex cavity extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome, and operably inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex cavity, and operably inject a second fuel-air mixture into the second combustion zone defined in the trapped vortex cavity to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex cavity. The steam injector operably injects steam into the trapped vortex cavity and the steam mixes with the combustion gases.Type: ApplicationFiled: August 22, 2023Publication date: February 27, 2025Inventors: Pradeep Naik, Clayton S. Cooper, Perumallu Vukanti, Michael A. Benjamin, Steven C. Vise, Sripathi Mohan
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Publication number: 20250067435Abstract: A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and a set of dilution passages. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The set of dilution passages extending through at least one of the inner liner or the outer liner. Each dilution passage of the set of dilution passages extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.Type: ApplicationFiled: November 11, 2024Publication date: February 27, 2025Inventors: Manampathy G. Giridharan, Pradeep Naik, Michael A. Benjamin
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Patent number: 12234987Abstract: A liner assembly for a combustor. The liner assembly includes a liner defining a combustion chamber of the combustor. The liner includes a looped section at a forward end of the liner. The looped section includes one or more bends such that the looped section forms a compliant joint and vibrations are dampened through the liner downstream of the looped section.Type: GrantFiled: July 11, 2022Date of Patent: February 25, 2025Assignee: GENERAL ELECTRIC COMPANYInventors: Ranganatha Narasimha Chiranthan, Hiranya Nath, Girish Kamath Cannanore, Ravindra Shankar Ganiger, Pradeep Naik, Saket Singh, Deepti Bhandari, Vijayaraj Sukumar
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Patent number: 12228286Abstract: A combustion section of a turbine engine having a primary combustion chamber and a secondary combustion chamber. The primary combustion chamber is defined, at least in part, by a combustor liner and a dome wall. A primary fuel nozzle having an outlet is located at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber. At least one opening located in an outer liner axially aft of the dome wall fluidly couples the secondary combustion chamber and the primary combustion chamber. A set of secondary fuel nozzles are fluidly coupled with the secondary combustion chamber.Type: GrantFiled: September 29, 2023Date of Patent: February 18, 2025Assignee: General Electric CompanyInventors: Pradeep Naik, Hiranya Kumar Nath, Perumallu Vukanti, Clayton S. Cooper, Steven C. Vise, Michael A. Benjamin, R Narasimha Chiranthan
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Patent number: 12228282Abstract: 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: January 10, 2024Date of Patent: February 18, 2025Assignee: General Electric CompanyInventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton Stuart Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
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Patent number: 12222104Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.Type: GrantFiled: May 10, 2022Date of Patent: February 11, 2025Assignee: General Electric CompanyInventors: Manampathy G. Giridharan, Michael T. Bucaro, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan
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Patent number: 12215870Abstract: A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.Type: GrantFiled: December 5, 2023Date of Patent: February 4, 2025Assignee: GENERAL ELECTRIC COMPANYInventors: Manampathy G. Giridharan, Pradeep Naik