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公开(公告)号：US20240200777A1
公开(公告)日：2024-06-20
申请号：US18104433
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pabitra Badhuk , Michael T. Bucaro , Pradeep Naik , Perumallu Vukanti , Arijit Sinha Roy , Sibtosh Pal , Bhavya Naidu Panduri , Aritra Chakraborty , Ajoy Patra , R Narasimha Chiranthan , Michael A. Benjamin
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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公开(公告)号：US12007114B1
公开(公告)日：2024-06-11
申请号：US18187359
申请日：2023-03-21
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Sibtosh Pal , Pradeep Naik , R Narasimha Chiranthan , Ajoy Patra , Michael T. Bucaro , Aritra Chakraborty , Arijit Sinha Roy , Pabitra Badhuk , Bhavya Naidu Panduri
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A first fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.
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公开(公告)号：US20240133552A1
公开(公告)日：2024-04-25
申请号：US18314418
申请日：2023-05-08
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Rimple Rangrej , Pradeep Naik , Saket Singh , Deepak Ghiya , Perumallu Vukanti
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00014
Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.
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公开(公告)号：US11959643B2
公开(公告)日：2024-04-16
申请号：US17340856
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rimple Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
CPC classification number: F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
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; 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; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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公开(公告)号：US20240102653A1
公开(公告)日：2024-03-28
申请号：US18529428
申请日：2023-12-05
Applicant: General Electric Company
Inventor： Saket Singh , Ravindra Shankar Ganiger , Hiranya Nath , Perumallu Vukanti , Ajoy Patra , Karthikeyan Sampath , Pradeep Naik , Rimple Rangrej , Veera Venkata Amarnath Manem
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03043
Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.
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Patent Agency Ranking
公开(公告)号：US11920796B2
公开(公告)日：2024-03-05
申请号：US17340856
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rimple Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
CPC classification number: F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
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; 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; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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公开(公告)号：US11846419B2
公开(公告)日：2023-12-19
申请号：US17810678
申请日：2022-07-05
Applicant: General Electric Company
Inventor： Saket Singh , Ravindra Shankar Ganiger , Hiranya Nath , Perumallu Vukanti , Ajoy Patra , Karthikeyan Sampath , Pradeep Naik , Rimple Rangrej , Veera Venkata Amarnath Manem
CPC classification number: F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03043
Abstract: A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.
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公开(公告)号：US20230366551A1
公开(公告)日：2023-11-16
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：US11815267B2
公开(公告)日：2023-11-14
申请号：US17809381
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Ranganatha Narasimha Chiranthan , Karthikeyan Sampath , Perumallu Vukanti , Rimple Rangrej , Ravindra Shankar Ganiger , Hiranya Nath
CPC classification number: F23R3/16 , F23R3/06 , F23R2900/00001 , F23R2900/03044 , F23R2900/03045
Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.
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公开(公告)号：US20230296251A1
公开(公告)日：2023-09-21
申请号：US17812278
申请日：2022-07-13
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Perumallu Vukanti , Pradeep Naik , Ravindra Shankar Ganiger , Daniel J. Kirtley , Arvind Namadevan , Ranganatha Narasimha Chiranthan , Hiranya Nath
IPC: F23R3/00
CPC classification number: F23R3/007 , F23R2900/00012 , F23R2900/00017 , F23R2900/03043
Abstract: A combustion liner assembly includes metal liner having a hot side and a cold side, a ceramic matrix composite (CMC) liner tile configured to provide a heat shield for the metal liner, the CMC liner tile having a different thermal conductivity than the metal liner, and a connection device configured to attach the CMC liner tile to the metal liner. The connection device accommodates the different thermal conductivity of the CMC liner tile and the metal liner. The connection device is free from a radial fastener exposed to hot gases on the hot side of the metal liner, and the connection device allows radial movement and axial movement between the metal liner and the CMC liner tile.
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