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公开(公告)号：US20240401807A1
公开(公告)日：2024-12-05
申请号：US18326665
申请日：2023-05-31
Applicant: General Electric Company
Inventor： Hiranya Nath , Michael A. Benjamin , Richard W. Stickles , Clayton S. Cooper , Steven C. Vise , Ranganatha Narasimha Chiranthan
Abstract: A turbine engine includes a combustor having a main combustion chamber, an annular dome positioned at a first angle α with respect to a longitudinal centerline axis of the combustor, and a secondary combustion chamber. The secondary combustion chamber is defined by a portion of the annular dome and an aft wall positioned at a second angle β with respect to the longitudinal centerline axis. A pilot mixer is disposed through the annular dome and injects a pilot mixer fuel-air mixture at a pilot mixer fuel-air mixture angle into the main combustion chamber and generates a first recirculation zone. A main mixer is disposed through the aft wall or the annular dome at the secondary combustion chamber. The main mixer injects a main mixer fuel-air mixture at a main mixer fuel-air mixture angle into the secondary combustion chamber to produce combustion gases and generates a second recirculation zone.
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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：US20240359816A1
公开(公告)日：2024-10-31
申请号：US18768636
申请日：2024-07-10
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , Michael A. Benjamin , Paul Burchell Glaser
CPC classification number: B64D37/32 , B64D27/10 , B64D37/04 , B64D37/30 , B64D37/34 , C06B23/008 , C06B43/00
Abstract: A hydrogen fuel including a safety marker and a method and apparatus for adding the safety marker to the hydrogen fuel. The hydrogen fuel may be stored in a tank in a liquid phase and then heated to at least one of a gaseous phase and a supercritical phase. The safety marker may be added to the hydrogen fuel when the hydrogen fuel is in the at least one of the gaseous phase and the supercritical phase after heating the hydrogen fuel. The hydrogen fuel may be delivered in the at least one of the gaseous phase and the supercritical phase to a power generator, such as a gas turbine engine. The safety marker may be a visual safety marker, such as a noble gas, or an odorant.
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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：US20240318597A1
公开(公告)日：2024-09-26
申请号：US18736667
申请日：2024-06-07
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
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Patent Agency Ranking
公开(公告)号：US20240310048A1
公开(公告)日：2024-09-19
申请号：US18673532
申请日：2024-05-24
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
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公开(公告)号：US20240309804A1
公开(公告)日：2024-09-19
申请号：US18673559
申请日：2024-05-24
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
CPC classification number: F02C3/22 , F02C7/22 , F23R3/28 , F05D2220/323 , F05D2240/35
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
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公开(公告)号：US11994295B2
公开(公告)日：2024-05-28
申请号：US17651642
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
Abstract: A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.
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公开(公告)号：US11898752B2
公开(公告)日：2024-02-13
申请号：US17932332
申请日：2022-09-15
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Michael A. Benjamin
CPC classification number: F23R3/002 , F23M20/005 , F23R2900/00014 , F23R2900/03042
Abstract: A hollow plank of a combustor liner defining a combustion chamber including an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of lateral walls coupled to the inner wall and the outer wall to define a cavity, and a partition wall connected to the plurality of lateral walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The one or more outer openings communicate with the first sub-cavity and communicate through a plurality of tubes with the second sub-cavity. The plurality of inner openings communicate with the second sub-cavity and communicate with the first sub-cavity through one or more bypass tubes. The first sub-cavity or the second sub-cavity, or both, are frequency tuned to reduce combustion dynamic frequencies.
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公开(公告)号：US20230408098A1
公开(公告)日：2023-12-21
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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