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公开(公告)号：US20250109853A1
公开(公告)日：2025-04-03
申请号：US18476595
申请日：2023-09-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Perumallu Vukanti , Ravindra Shankar Ganiger , Sahana Narasimhan Suresh , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Sripathi Mohan , Hiranya Kumar Nath
Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section includes a primary combustor liner including an inner liner and an outer liner. A dome wall and a primary dome inlet are located in the dome wall. The outer liner defines at least one opening downstream from the primary dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.
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公开(公告)号：US12215870B2
公开(公告)日：2025-02-04
申请号：US18529360
申请日：2023-12-05
Applicant: General Electric Company
Inventor： Manampathy G. Giridharan , Pradeep Naik
Abstract: A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.
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公开(公告)号：US20250020323A1
公开(公告)日：2025-01-16
申请号：US18435033
申请日：2024-02-07
Applicant: General Electric Company
Inventor： Saket Singh , Pradeep Naik , Rimple Rangrej , Ranganatha Narasimha , Krishnendu Chakraborty , Shai Birmaher
Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.
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公开(公告)号：US12163664B2
公开(公告)日：2024-12-10
申请号：US18342960
申请日：2023-06-28
Applicant: General Electric Company
Inventor： Ranjeet Kumar Mishra , Jayanth Sekar , Pradeep Naik , Gregory A. Boardman , Randall C. Boehm
Abstract: A premixer for a combustor includes: a centerbody having a hollow interior cavity; a swirler assembly radially outward of the centerbody; a peripheral wall disposed radially outward of the centerbody and the swirler assembly such that a mixing duct is defined between the peripheral wall and the centerbody, downstream from the swirler assembly; an annular splitter radially inward of the swirler assembly and radially outward of the centerbody such that a radial gap is defined between the splitter and an outer surface of the centerbody, wherein the splitter includes a trailing edge which extends axially aft of the swirler assembly; a fuel gallery disposed inside the interior cavity of the centerbody; and at least one fuel injector extending outward from the fuel gallery and passing through an injector port communicating with the outer surface of the splitter.
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公开(公告)号：US12158270B2
公开(公告)日：2024-12-03
申请号：US18104408
申请日：2023-02-01
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , R Narasimha Chiranthan , Ajoy Patra , Arijit Sinha Roy , Pabitra Badhuk , Aritra Chakraborty , Bhavya Naidu Panduri , Michael T. Bucaro , Sibtosh Pal
Abstract: A combustor comprising a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup of the set of fuel cups. The set of fuel cups circumferentially spaced along the dome wall relative to the combustor centerline. The set of dilution passages terminating in a plurality of slots spaced about the corresponding fuel cup in the set of fuel cups.
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Patent Agency Ranking
公开(公告)号：US12152777B2
公开(公告)日：2024-11-26
申请号：US17340703
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Perumallu Vukanti , Daniel J. Kirtley , Karthikeyan Sampath , Shai Birmaher , Pradeep Naik , Rajendra Mahadeorao Wankhade , Michael Anthony Benjamin , Veeraraju Vanapalli , Deepak Ghiya
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.
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公开(公告)号：US12146660B2
公开(公告)日：2024-11-19
申请号：US17340654
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Daniel J. Kirtley , Shai Birmaher , Veeraraju Vanapalli , Karthikeyan Sampath , Deepak Ghiya , Perumallu Vukanti , Rajendra Mahadeorao Wankhade , Pradeep Naik
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.
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公开(公告)号：US12085283B2
公开(公告)日：2024-09-10
申请号：US17340764
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Daniel J. Kirtley , Shai Birmaher , Veeraraju Vanapalli , Karthikeyan Sampath , Deepak Ghiya , Perumallu Vukanti , Rajendra Mahadeorao Wankhade , Pradeep Naik , Rimple Rakeshkumar Rangrej , Saket Singh
CPC classification number: F23R3/42 , F02C3/02 , F02C3/14 , F05D2220/32 , F05D2240/35
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.
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公开(公告)号：US12085281B2
公开(公告)日：2024-09-10
申请号：US18350205
申请日：2023-07-11
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：US12072103B2
公开(公告)日：2024-08-27
申请号：US17699735
申请日：2022-03-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Manampathy G. Giridharan , Ajoy Patra , R Narasimha Chiranthan
CPC classification number: F23R3/286 , F23R3/14 , F23R2900/03042
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel premixer. The fuel premixer can include an annular shroud defining an interior, a center body located within the interior, and an annular swirler located within the interior.
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