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公开(公告)号：US20220372915A1
公开(公告)日：2022-11-24
申请号：US17323088
申请日：2021-05-18
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Steven Clayton Vise , Clayton S. Cooper , Michael A. Benjamin
IPC: F02C7/22
Abstract: A gas turbine engine that is configured to mitigate fuel coupled dynamics. The engine includes a combustor, a fuel delivery system, a fuel manifold line; and a device configured to mitigate fuel coupled dynamics. The device is attached to the fuel manifold line and includes a housing and a reflector. The housing includes a wall and the wall defines a housing surface that is configured to reflect waves conducted by fuel within the fuel delivery system. The reflector is positioned within the housing and the reflector includes an anterior surface that is configured to reflect waves conducted by fuel within the fuel delivery system such that wave the reflected waves can strike the surface.
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公开(公告)号：US20220372913A1
公开(公告)日：2022-11-24
申请号：US17324451
申请日：2021-05-19
Applicant: General Electric Company
Inventor： Hiranya Nath , Michael A. Benjamin , Rajendra Wankhade , Hari Chandra
Abstract: A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.
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公开(公告)号：US20220349581A1
公开(公告)日：2022-11-03
申请号：US17860990
申请日：2022-07-08
Applicant: General Electric Company
Inventor： Brett A. Rich , Michael A. Benjamin , Nicholas R. Overman , Aaron J. Glaser
Abstract: In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture configured to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first channel directing a first air stream into the fuel conduit; and a second channel directing a second air stream into the fuel conduit. The first air stream and the second air stream cooperatively shape the fuel jet coming out of the fuel window.
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公开(公告)号：US11421885B2
公开(公告)日：2022-08-23
申请号：US17231771
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：US11408610B1
公开(公告)日：2022-08-09
申请号：US17166477
申请日：2021-02-03
Applicant: General Electric Company
Inventor： Brett A. Rich , Michael A. Benjamin , Nicholas R. Overman , Aaron J. Glaser
Abstract: In some embodiments, systems, apparatuses and methods are provided herein useful for spraying fuel in an augmented gas turbine engine. The embodiments may include a spray bar with a fuel injection aperture to inject a fuel jet into a fuel conduit; the fuel conduit having a fuel window to discharge the fuel jet into a core exhaust flow of an augmented gas turbine engine; a first airflow conduit having a first orifice to discharge a first air stream into the core exhaust flow; and a second airflow conduit having a second orifice to discharge a second air stream into the core exhaust flow. The first orifice and the second orifice may be paired with the fuel window to cooperatively shape the fuel jet coming out of the fuel window.
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Patent Agency Ranking
公开(公告)号：US20220178540A1
公开(公告)日：2022-06-09
申请号：US17115877
申请日：2020-12-09
Applicant: General Electric Company
Inventor： Hari Ravi Chandra , Arvind Kumar Rao , Shai Birmaher , Jayanth Sekar , Gurunath Gandikota , Michael A. Benjamin
Abstract: A mixing assembly for a combustor, including: a pilot mixer and a pilot fuel nozzle; a main mixer including: a main housing surrounding the pilot mixer; a fuel manifold positioned between the pilot housing and the main housing; a mixer foot extending outward from a forward end of the main housing; a main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and coupled to the mixer foot; and a main fuel ring in the mixing channel downstream of the mixer foot connected to the main housing by main fuel vanes, at least one of the main fuel ring and the main fuel vanes including fuel injection ports positioned to discharge fuel into a central portion of the mixing channel, wherein the mixer foot extends farther from the main housing than the main fuel ring.
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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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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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