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公开(公告)号：US11905837B2
公开(公告)日：2024-02-20
申请号：US17656106
申请日：2022-03-23
Applicant: General Electric Company
Inventor： Nicholas R. Overman
IPC: F01D11/00
CPC classification number: F01D11/005 , F05D2240/57 , F05D2260/38
Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.
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公开(公告)号：US11802693B2
公开(公告)日：2023-10-31
申请号：US17232653
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Allen M. Danis , Nicholas R. Overman , Steven Clayton Vise , Michael Anthony Benjamin , James Matthew Rogers
CPC classification number: F23R3/14 , F23D14/62 , F23R3/286 , F23D2206/10 , F23D2900/14021 , F23D2900/14701
Abstract: A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline, each primary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; wherein the second vane angle is different from the first vane angle; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline.
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公开(公告)号：US20220243915A1
公开(公告)日：2022-08-04
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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公开(公告)号：US20240247595A1
公开(公告)日：2024-07-25
申请号：US18444100
申请日：2024-02-16
Applicant: General Electric Company
Inventor： Nicholas R. Overman
IPC: F01D11/00
CPC classification number: F01D11/005 , F05D2240/57 , F05D2260/38
Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.
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公开(公告)号：US11920791B1
公开(公告)日：2024-03-05
申请号：US18166600
申请日：2023-02-09
Applicant: General Electric Company
Inventor： Nicholas R. Overman
CPC classification number: F23R3/16 , F02C7/00 , F23R3/002 , F05D2220/32 , F05D2240/35 , F05D2260/14
Abstract: A trapped vortex reverse flow combustor for a gas turbine includes a first dome structure having a plurality of first-dome vortex driver airflow openings for providing a first vortex generating mid airflow therethrough to a trapped vortex cavity. A second dome structure is arranged downstream of the first dome structure and includes a plurality of second-dome vortex driver airflow openings providing a first vortex generating outer airflow therethrough to the trapped vortex cavity, and a plurality of primary driver airflow openings providing a primary driver airflow therethrough radially inward of the trapped vortex cavity.
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Patent Agency Ranking
公开(公告)号：US11898755B2
公开(公告)日：2024-02-13
申请号：US17805983
申请日：2022-06-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Nicholas R. Overman
CPC classification number: F23R3/346 , F23R3/002 , F23R3/26 , F23R2900/00014 , F23R2900/03044
Abstract: A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.
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公开(公告)号：US11815025B2
公开(公告)日：2023-11-14
申请号：US17315028
申请日：2021-05-07
Applicant: General Electric Company
Inventor： Nicholas R. Overman
Abstract: A fuel nozzle for a combustor may include a primary fuel passage having a primary fuel outlet. A secondary fuel passage having a secondary fuel outlet. A valve located within the secondary fuel passage. The valve may include a stationary hub having a plurality of first angled surfaces. The valve may include a movable sleeve having a plurality of second angled surfaces. Each of the plurality of first angled surfaces aligns axially with a respective one of the plurality of second angled surfaces to define a slot therebetween. The valve is movable between a plurality of positions to open, to close, or to partially open the slots.
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公开(公告)号：US20230266002A1
公开(公告)日：2023-08-24
申请号：US17651644
申请日：2022-02-18
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Kwanwoo Kim , Saket Singh , Perumallu Vukanti , Karthikeyan Sampath , Steven C. Vise , Nicholas R. Overman , Michael A. Benjamin
CPC classification number: F23D11/383 , F23R3/14 , F23R3/283 , F23R3/286 , F23R3/50 , F23R2900/03041 , F23R2900/03042
Abstract: A swirler assembly includes a swirler having a primary swirler with a primary swirler venturi, a swirler ferrule plate connected upstream to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an annular pressure drop cavity with oxidizer inlet orifices in fluid communication with the swirler, and at least one outlet orifice in fluid communication with the primary swirler venturi. A second flow of oxidizer to the swirler incurs a first pressure drop, a third flow of the oxidizer from the swirler to the annular pressure drop cavity incurs a second pressure drop, and a fourth flow of the oxidizer from the annular pressure drop cavity to the primary swirler venturi incurs a third pressure drop.
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公开(公告)号：US20230400187A1
公开(公告)日：2023-12-14
申请号：US17805983
申请日：2022-06-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Nicholas R. Overman
CPC classification number: F23R3/002 , F23R3/346 , F23R2900/00014 , F23R2900/03044
Abstract: A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.
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公开(公告)号：US11828469B2
公开(公告)日：2023-11-28
申请号：US17653376
申请日：2022-03-03
Applicant: General Electric Company
Inventor： Nicholas R. Overman , Aaron J. Glaser
Abstract: An adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber, a fuel injector, and one or more chutes. The combustion chamber is defined by an outer liner, an inner liner, and a dome, and includes a primary combustion zone within the combustion chamber defining a vortex cavity for a trapped vortex, the vortex cavity having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The fuel injector injects a fuel into the primary combustion zone. The one or more chutes provide an air flow to the primary combustion zone and/or the secondary combustion zone. A feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine.
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