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公开(公告)号：US20250035304A1
公开(公告)日：2025-01-30
申请号：US18913347
申请日：2024-10-11
Applicant: General Electric Company
Inventor： Steven C. Vise , Clayton S. Cooper , Michael A. Benjamin , Pradeep Naik , Kwanwoo Kim , Shai Birmaher , Perumallu Vukanti , Saket Singh , Karthikeyan Sampath
Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.
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公开(公告)号：US12163660B2
公开(公告)日：2024-12-10
申请号：US18484987
申请日：2023-10-11
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Ajoy Patra
IPC: F23R3/06
Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.
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公开(公告)号：US20240401527A1
公开(公告)日：2024-12-05
申请号：US18497199
申请日：2023-10-30
Applicant: General Electric Company
Inventor： Pradeep Naik , Sibtosh Pal , Saket Singh
IPC: F02C7/04
Abstract: A gas turbine includes a combustion section, and a diffuser arranged to provide a flow of compressed air from a compressor to the combustion section. The diffuser includes a steam injection system that provides a flow of steam from the diffuser to the combustion section.
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公开(公告)号：US20240247807A1
公开(公告)日：2024-07-25
申请号：US18585509
申请日：2024-02-23
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rample 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：US11920790B2
公开(公告)日：2024-03-05
申请号：US17649220
申请日：2022-01-28
Applicant: General Electric Company
Inventor： Saket Singh , Pradeep Naik , Rimple Rangrej , Ranganatha Narasimha Chiranthan , 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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Patent Agency Ranking
公开(公告)号：US20240044493A1
公开(公告)日：2024-02-08
申请号：US18484987
申请日：2023-10-11
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Ajoy Patra
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.
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公开(公告)号：US20230408093A1
公开(公告)日：2023-12-21
申请号：US18460078
申请日：2023-09-01
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Karthikeyan Sampath , Perumallu Vukanti , Allen M. Danis , Scott M. Bush , Steven Clayton Vise , Hari Ravi Chandra , Rimple Rangrej , Saket Singh , Pradeep Naik , Neeraj Kumar Mishra , Arvind Kumar Rao , Balasubramaniam Venkatanarayanan , Ranjeet Kumar Mishra
Abstract: A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.
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公开(公告)号：US20230288066A1
公开(公告)日：2023-09-14
申请号：US18320529
申请日：2023-05-19
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
CPC classification number: F23R3/06 , F23R3/045 , F23R3/002 , F23R2900/03043
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 array having a plurality of dilution passages, each dilution passage of the plurality of dilution passages having a concatenated geometry repeating in a predetermined pattern and extending circumferentially around the liner body. The dilution passage integrates 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 injects the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor. The dilution array is repeated along an axial length of the liner body.
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公开(公告)号：US11725819B2
公开(公告)日：2023-08-15
申请号：US17682373
申请日：2022-02-28
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：US20230175695A1
公开(公告)日：2023-06-08
申请号：US17653399
申请日：2022-03-03
Applicant: General Electric Company
Inventor： Rimple Rangrej , Saket Singh , Pradeep Naik , Ajoy Patra
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.
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