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公开(公告)号：US20230313992A1
公开(公告)日：2023-10-05
申请号：US17811771
申请日：2022-07-11
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Hiranya Nath , Girish Kamath Cannanore , Ravindra Shankar Ganiger , Pradeep Naik , Saket Singh , Deepti Bhandari , Vijayaraj Sukumar
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/03043 , F23R2900/00014 , F23R2900/00017
Abstract: A liner assembly for a combustor. The liner assembly includes a liner defining a combustion chamber of the combustor. The liner includes a looped section at a forward end of the liner. The looped section includes one or more bends such that the looped section forms a compliant joint and vibrations are dampened through the liner downstream of the looped section.
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公开(公告)号：US20230304665A1
公开(公告)日：2023-09-28
申请号：US18302346
申请日：2023-04-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ajoy Patra , Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , R Narasimha Chiranthan , Manampathy G. Giridharan , Michael A. Benjamin , Clayton S. Cooper
CPC classification number: F23R3/286 , F02C7/264 , F23D14/64 , F23R3/045 , F23R3/50 , F05D2240/35 , F05D2260/99 , F23D2207/00
Abstract: A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.
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公开(公告)号：US20230296250A1
公开(公告)日：2023-09-21
申请号：US17740443
申请日：2022-05-10
Applicant: General Electric Company
Inventor： Manampathy G. Giridharan , Michael T. Bucaro , Pradeep Naik , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R2900/03044
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 combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.
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公开(公告)号：US11754284B2
公开(公告)日：2023-09-12
申请号：US17663098
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
Abstract: A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The concatenated geometry has a plurality of discrete dilution holes, an annular slot, and a fence concatenated with the plurality of discrete dilution holes. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the plurality of discrete dilution holes from the cold side to the hot side and a second dilution air flow flowing through the annular slot from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.
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公开(公告)号：US20230194095A1
公开(公告)日：2023-06-22
申请号：US17700852
申请日：2022-03-22
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Michael T. Bucaro , Ajoy Patra , Manampathy G. Giridharan , Steven C. Vise , R Narasimha Chiranthan , Michael A. Benjamin , Clayton S. Cooper
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. Increasing efficiency and emission needs require the use of alternative fuels, which combust at higher temperatures and faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
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Patent Agency Ranking
公开(公告)号：US20230194087A1
公开(公告)日：2023-06-22
申请号：US17663311
申请日：2022-05-13
Applicant: General Electric Company
Inventor： Saket Singh , Pradeep Naik , Rimple Rangrej , Shai Birmaher , Ranganatha Narasimha Chiranthan , Ajoy Patra , Ravindra Shankar Ganiger , Hiranya Nath
Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.
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公开(公告)号：US20230148305A1
公开(公告)日：2023-05-11
申请号：US17663095
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
Abstract: A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The concatenated geometry has a plurality of discrete dilution holes, an annular slot, and a plurality of dilution inserts. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.
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公开(公告)号：US20230146319A1
公开(公告)日：2023-05-11
申请号：US17663098
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
Abstract: A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The concatenated geometry has a plurality of discrete dilution holes, an annular slot, and a fence concatenated with the plurality of discrete dilution holes. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the plurality of discrete dilution holes from the cold side to the hot side and a second dilution air flow flowing through the annular slot from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.
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公开(公告)号：US11578868B1
公开(公告)日：2023-02-14
申请号：US17808158
申请日：2022-06-22
Applicant: General Electric Company
Inventor： Krishnendu Chakraborty , Pradeep Naik , Saket Singh , Shai Birmaher , Rimple Rangrej , Daniel J. Kirtley
Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. At least one of the outer liner and the inner liner has an upstream liner portion and a downstream liner portion with an annular gap therebetween. At least one dilution flow assembly is arranged to bridge across the annular gap. The at least one dilution flow assembly includes an upstream liner panel and a downstream liner panel with a dilution opening provided between the upstream liner panel and the downstream liner panel, and a plurality of dilution fence members arranged within the dilution opening and extending into a combustion chamber. The plurality of dilution fence members are arranged in successive arrangement in a circumferential direction and are arranged such that successive dilution fence members are alternatingly offset in an axial direction.
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200.发明申请公开(公告)号：US20220412563A1
公开(公告)日：2022-12-29
申请号：US17397396
申请日：2021-08-09
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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