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公开(公告)号：US20220412550A1
公开(公告)日：2022-12-29
申请号：US17396155
申请日：2021-08-06
Applicant: General Electric Company
Inventor： Steven C. Vise , Clayton S. Cooper , Michael A. Benjamin , Pradeep Naik , Kwanwoo Kim , Shai Birmaher , Perumallu Vukanti , Saket Singh , Karthikeyan Sampath
Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.
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公开(公告)号：US20220333781A1
公开(公告)日：2022-10-20
申请号：US17232433
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Hari Ravi Chandra , Jayanth Sekar , Gurunath Gandikota , Michael A. Benjamin
Abstract: A mixing assembly for a combustor includes: a pilot mixer including a pilot housing extending along a mixer centerline and a pilot fuel nozzle; a main mixer surrounding the pilot mixer; a fuel manifold between the pilot and main mixers; a mixer foot extending from a main housing of the main mixer; a main swirler body surrounding the main housing defining a mixing channel between the main housing and the main swirler body; and a main fuel ring in the mixing channel connected to the main housing by main fuel vanes, at least one of the main fuel ring and main fuel vanes including fuel injection ports for discharging fuel into the mixing channel, wherein the fuel injection ports are disposed non-uniformly relative to the mixer centerline, so as to produce a static pressure difference therebetween in response to mixer air flow passing around the main fuel ring.
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公开(公告)号：US11421884B2
公开(公告)日：2022-08-23
申请号：US17231750
申请日：2021-04-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Duane Douglas Thomsen , Michael A. Benjamin
Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.
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公开(公告)号：US20250075911A1
公开(公告)日：2025-03-06
申请号：US18949096
申请日：2024-11-15
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：US20250075910A1
公开(公告)日：2025-03-06
申请号：US18952330
申请日：2024-11-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Joseph Zelina , Sripathi Mohan , Perumallu Vukanti , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Karthikeyan Sampath
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20250067438A1
公开(公告)日：2025-02-27
申请号：US18536610
申请日：2023-12-12
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Michael David Clark
Abstract: A heat shield for a combustor of a gas turbine engine. The heat shield includes an annular ring having an axial direction, a radial direction, and a circumferential direction. The annular ring includes a plurality of circumferential segments. Each circumferential segment of the plurality of circumferential segments is disconnected from an adjacent circumferential segment of the plurality of circumferential segments to allow for thermal growth of each circumferential segment during operation of the combustor.
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公开(公告)号：US20250067214A1
公开(公告)日：2025-02-27
申请号：US18501484
申请日：2023-11-03
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Saket Singh , Michael A. Benjamin , Sripathi Mohan , Clayton S. Cooper , Rajendra Wankhade , Hiranya Nath , Nicholas R. Overman , Steven C. Vise
Abstract: 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.
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28.发明授权公开(公告)号：US12215869B2
公开(公告)日：2025-02-04
申请号：US18452958
申请日：2023-08-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nayan Vinod Patel , Michael A. Benjamin
Abstract: 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 combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
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公开(公告)号：US20250020324A1
公开(公告)日：2025-01-16
申请号：US18435282
申请日：2024-02-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Manampathy G. Giridharan , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Michael T. Bucaro , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , R Narasimha Chiranthan
Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.
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公开(公告)号：US12196422B2
公开(公告)日：2025-01-14
申请号：US17664971
申请日：2022-05-25
Applicant: General Electric Company
Inventor： Saket Singh , Rimple Rangrej , Pradeep Naik , Michael A. Benjamin , Joseph Zelina
Abstract: A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.
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