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公开(公告)号：US11781753B2
公开(公告)日：2023-10-10
申请号：US17809629
申请日：2022-06-29
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Sripathi Mohan , Girish Kamath Cannanore
CPC classification number: F23R3/60 , F23M5/04 , F23R3/002 , F23R3/50 , F23R2900/00014 , F23R2900/00017 , F23R2900/03044
Abstract: A combustor for a gas turbine includes a dome, and a deflector connected to the dome to define a baffle cavity therebetween, the deflector having a deflector cold side adjacent to the baffle cavity and a deflector hot side adjacent to a combustion chamber. At least one dome-deflector connecting member connects the dome and the deflector to each other. The dome-deflector connecting member forms a flexible joint between the dome and the deflector.
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公开(公告)号：US12270546B2
公开(公告)日：2025-04-08
申请号：US18324313
申请日：2023-05-26
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Asim Ghosal , Sripathi Mohan , Nageswar Ganji
Abstract: A dome-deflector assembly for a combustor of a gas turbine includes a dome portion having a dome-side swirler opening therethrough, and a deflector portion having a deflector-side swirler opening therethrough. The dome portion and the deflector portion are connected together to form a dome-deflector cavity therebetween. The deflector portion includes a first-side surface and a second-side surface, the second-side surface being arranged within the dome-deflector cavity, and the second-side surface including a plurality of stress-relief contours arranged in a pattern about the deflector-side swirler opening.
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公开(公告)号：US12173898B1
公开(公告)日：2024-12-24
申请号：US18486368
申请日：2023-10-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Pradeep Naik , Joseph Zelina , Sripathi Mohan , Perumallu Vukanti , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Karthikeyan Sampath
Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.
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公开(公告)号：US20240328360A1
公开(公告)日：2024-10-03
申请号：US18742260
申请日：2024-06-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Michael T. Bucaro , Manampathy G. Giridharan , Pradeep Naik , Sripathi Mohan , Michael A. Benjamin , Steven C. Vise , Ajoy Patra , Perumallu Vukanti , R Narasimha Chiranthan
Abstract: A turbine engine and method of operation with a combustor as shown and described. The turbine engine including a combustor comprising an annular array of rich cups and an annular array of lean cups. A method for controlling nitrogen oxides including injecting a fuel/air mixture from the lean cups and the rich cups.
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公开(公告)号：US20240133555A1
公开(公告)日：2024-04-25
申请号：US18314414
申请日：2023-05-08
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Sripathi Mohan , Perumallu Vukanti , Kwanwoo Kim
IPC: F23R3/42
CPC classification number: F23R3/42 , F23R2900/00014
Abstract: A combustor for a turbomachine engine. The combustor includes a combustion chamber, and a cowl having an annular shape that is symmetric around a centerline axis of the turbomachine engine. The cowl includes a hollow cavity that is in fluid communication with the combustion chamber. The hollow cavity is a damper that reduces combustion dynamics of the combustor.
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Patent Agency Ranking
公开(公告)号：US20230296245A1
公开(公告)日：2023-09-21
申请号：US17655196
申请日：2022-03-17
Applicant: General Electric Company
Inventor： Kwanwoo Kim , Varun Lakshmanan , Sripathi Mohan , Vivekta Sharma
CPC classification number: F23D14/62 , F23D14/78 , F23D14/70 , F23R3/14 , F23D2214/00
Abstract: A flare cone for a mixer assembly includes an annular conical wall extending circumferentially about a mixer assembly centerline, the annular conical wall including a conical inner surface defining a conical opening of the annular conical wall, and an annular axial wall extending in a longitudinal direction with respect to the mixer assembly centerline, the annular axial wall disposed at a radially outward portion of the annular conical wall and connected to the annular conical wall. The annular conical wall and the annular axial wall define an annular step circumferentially about the mixer assembly centerline and extending upstream in the longitudinal direction between a downstream end of the annular conical wall and an aft surface of the annular axial wall.
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公开(公告)号：US11761631B2
公开(公告)日：2023-09-19
申请号：US17806576
申请日：2022-06-13
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Sripathi Mohan
CPC classification number: F23R3/002 , F23R3/007 , F23R3/50 , F23R2900/00017 , F23R2900/03043
Abstract: A dome structure for a combustor of a gas turbine includes a frame structure extending circumferentially about a combustor centerline axis, and a plurality of integrated dome-deflector plate members mounted to the frame structure. Each of the plurality of integrated dome-deflector plate members includes a dome wall, a deflector wall, and a plurality of side walls connecting the dome wall and the deflector wall to each other. A cavity is defined by the dome wall, the deflector wall, and the plurality of side walls.
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公开(公告)号：US11747019B1
公开(公告)日：2023-09-05
申请号：US17929359
申请日：2022-09-02
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Michael A. Benjamin , Steven C. Vise , Perumallu Vukanti , Sripathi Mohan , Rimple Rangrej
CPC classification number: F23R3/06 , F23R3/16 , F23R3/46 , F23R3/50 , F23R2900/03043
Abstract: A combustor liner has an annular outer liner and an annular inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The annular outer liner and the annular inner liner each has a converging-diverging section extending into the dilution zone of the combustion chamber that form a throat between them. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat for providing a flow of an oxidizer through a respective liner to the dilution zone of the combustion chamber.
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公开(公告)号：US11635209B2
公开(公告)日：2023-04-25
申请号：US17649128
申请日：2022-01-27
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Sripathi Mohan , Karthikeyan Sampath , Steven C. Vise , Shai Birmaher , Saket Singh
Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.
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公开(公告)号：US20230053389A1
公开(公告)日：2023-02-23
申请号：US17649128
申请日：2022-01-27
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Pradeep Naik , Sripathi Mohan , Karthikeyan Sampath , Steven C. Vise , Shai Birmaher , Saket Singh
Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.
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