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公开(公告)号：US12234987B2
公开(公告)日：2025-02-25
申请号：US17811771
申请日：2022-07-11
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Hiranya Nath , Girish Kamath Cannanore , Ravindra Shankar Ganiger , Pradeep Naik , Saket Singh , Deepti Bhandari , Vijayaraj Sukumar
Abstract: 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.
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公开(公告)号：US12228286B1
公开(公告)日：2025-02-18
申请号：US18477597
申请日：2023-09-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Hiranya Kumar Nath , Perumallu Vukanti , Clayton S. Cooper , Steven C. Vise , Michael A. Benjamin , R Narasimha Chiranthan
Abstract: 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.
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3.发明授权公开(公告)号：US12215866B2
公开(公告)日：2025-02-04
申请号：US17734469
申请日：2022-05-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Manampathy G. Giridharan , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in axial flow arrangement. The combustion section can include a combustor having a fuel-air mixer. The fuel-air mixer can include a body with at least an air passage, as well as a set of mixing passages.
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公开(公告)号：US12181151B2
公开(公告)日：2024-12-31
申请号：US17389030
申请日：2021-07-29
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik
Abstract: 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.
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公开(公告)号：US20240410582A1
公开(公告)日：2024-12-12
申请号：US18809634
申请日：2024-08-20
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Varun S. Lakshmanan , Michael T. Bucaro , Pradeep Naik , Steven C. Vise , Michael A. Benjamin
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20240401809A1
公开(公告)日：2024-12-05
申请号：US18805691
申请日：2024-08-15
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Clayton S. Cooper , Michael A. Benjamin , Michael T. Bucaro , Manampathy G. Giridharan , Steven C. Vise , Ajoy Patra , Saket Singh , R Narasimha Chiranthan
Abstract: 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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
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公开(公告)号：US12152779B1
公开(公告)日：2024-11-26
申请号：US18453500
申请日：2023-08-22
Applicant: General Electric Company
Inventor： Pradeep Naik , Clayton S. Cooper , Perumallu Vukanti , Michael A. Benjamin , Steven C. Vise , Sripathi Mohan
Abstract: 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.
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公开(公告)号：US12146662B2
公开(公告)日：2024-11-19
申请号：US18482949
申请日：2023-10-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Manampathy G. Giridharan , Ajoy Patra , Pradeep Naik , R Narasimha Chiranthan , Perumallu Vukanti , Michael T. Bucaro
IPC: F23R3/28
Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.
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公开(公告)号：US12130016B1
公开(公告)日：2024-10-29
申请号：US18326647
申请日：2023-05-31
Applicant: General Electric Company
Inventor： Hiranya Nath , Clayton S. Cooper , Steven C. Vise , Michael A. Benjamin , Pradeep Naik , Ranganatha Narasimha Chiranthan , Perumallu Vukanti , Sibtosh Pal
Abstract: A combustor for a turbine engine includes a main combustion chamber, an annular dome, and a secondary combustion chamber positioned downstream of the annular dome. A plurality of first mixing assemblies are disposed through the annular dome and include a pilot mixer. The pilot mixer injects a pilot mixer fuel-air mixture axially into the main combustion chamber and generates a first recirculation zone within the main combustion chamber. A plurality of second mixing assemblies are disposed at the secondary combustion chamber axially aft of the first mixing assemblies and include a main mixer. The main mixer injects a main mixer fuel-air mixture into the secondary combustion chamber to produce combustion gases and to generate a second recirculation zone within the secondary combustion chamber axially aft of the first recirculation zone. The secondary combustion chamber injects the combustion gases into the main combustion chamber.
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公开(公告)号：US12123595B2
公开(公告)日：2024-10-22
申请号：US17820373
申请日：2022-08-17
Applicant: General Electric Company
Inventor： Hiranya Nath , Karthikeyan Sampath , Perumallu Vukanti , Ravindra Shankar Ganiger , Pradeep Naik
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A combustor liner for a gas turbine includes a liner at least partially defining a combustion chamber. The liner includes a plurality of dilution openings therethrough, at least one dilution opening of the plurality of dilution openings defined by (a) a main dilution opening portion defining a main dilution opening perimeter, and (b) a plurality of secondary dilution opening portions arranged about the main dilution opening perimeter and extending outward from the main dilution opening portion.
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