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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：US20230143185A1
公开(公告)日：2023-05-11
申请号：US17663103
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
IPC: F23R3/06
CPC classification number: F23R3/06 , 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：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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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：US20240247802A1
公开(公告)日：2024-07-25
申请号：US18598467
申请日：2024-03-07
Applicant: General Electric Company
Inventor： Vijayaraj Sukumar , Perumallu Vukanti , Pradeep Naik , Ajoy Patra , Karthikeyan Sampath , Rimple Rangrej , Hiranya Nath , Krishnendu Chakraborty , Narasimhan S. Sahana , Saket Singh , Ravindra Shankar Ganiger
CPC classification number: F23R3/002 , F23R3/60 , F23R3/04 , F23R3/10 , F23R2900/00017 , F23R2900/03045
Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.
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Patent Agency Ranking
公开(公告)号：US20230324047A1
公开(公告)日：2023-10-12
申请号：US17812897
申请日：2022-07-15
Applicant: General Electric Company
Inventor： Vijayaraj Sukumar , Perumallu Vukanti , Pradeep Naik , Ajoy Patra , Karthikeyan Sampath , Rimple Rangrej , Hiranya Nath , Krishnendu Chakraborty , Narasimhan S. Sahana , Saket Singh , Ravindra Shankar Ganiger
CPC classification number: F23R3/002 , F23R2900/03045 , F23R2900/00017 , F23R3/60
Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.
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公开(公告)号：US11686473B2
公开(公告)日：2023-06-27
申请号：US17663103
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
CPC classification number: F23R3/06 , F23R3/002 , F23R3/045 , 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：US20230144971A1
公开(公告)日：2023-05-11
申请号：US17663093
申请日：2022-05-12
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
CPC classification number: F23R3/06 , F23R3/16 , F23R2900/03045
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 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：US20230094199A1
公开(公告)日：2023-03-30
申请号：US17649218
申请日：2022-01-28
Applicant: General Electric Company
Inventor： Pradeep Naik , Shai Birmaher , Saket Singh , Rimple Rangrej , Krishnendu Chakraborty
IPC: F23R3/26
Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. The outer liner has an annular outer liner slot dilution opening, with a plurality of outer liner swirl vanes disposed within the annular outer liner slot dilution opening. The inner liner of the combustor liner includes an annular inner liner slot dilution opening, and also includes a plurality of inner liner swirl vanes disposed within the annular inner liner slot dilution opening.
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公开(公告)号：US11927349B2
公开(公告)日：2024-03-12
申请号：US17812897
申请日：2022-07-15
Applicant: General Electric Company
Inventor： Vijayaraj Sukumar , Perumallu Vukanti , Pradeep Naik , Ajoy Patra , Karthikeyan Sampath , Rimple Rangrej , Hiranya Nath , Krishnendu Chakraborty , Narasimhan S. Sahana , Saket Singh , Ravindra Shankar Ganiger
CPC classification number: F23R3/002 , F23R3/60 , F23R3/04 , F23R3/10 , F23R2900/00017 , F23R2900/03045
Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.
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