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公开(公告)号：US11747018B2
公开(公告)日：2023-09-05
申请号：US17587169
申请日：2022-01-28
Applicant: General Electric Company
Inventor： Perumallu Vukanti , Varun S. Lakshmanan , Michael T. Bucaro , Pradeep Naik , Steven C. Vise , Michael A. Benjamin
CPC classification number: F23R3/06 , F23R3/16 , F23R3/28 , F23R2900/03044
Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.
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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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53.发明公开公开(公告)号：US20230194093A1
公开(公告)日：2023-06-22
申请号：US17717739
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Michael T. Bucaro , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , R Narasimha Chiranthan , Clayton S. Cooper , Michael A. Benjamin , Steven C. Vise , Manampathy G. Giridharan , Krishnakumar Venkatesan
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. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
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公开(公告)号：US20230194092A1
公开(公告)日：2023-06-22
申请号：US17682510
申请日：2022-02-28
Applicant: General Electric Company
Inventor： Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Steven C. Vise , Ajoy Patra , R Narasimha Chiranthan , Manampathy G. Giridharan , Michael A. Benjamin , Clayton S. Cooper , Dharmaraj Pachaiappan
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 meeting emission needs can be met with the use of alternative fuels, which combust at higher temperatures or higher 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：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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Patent Agency Ranking
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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公开(公告)号：US11578869B2
公开(公告)日：2023-02-14
申请号：US17325938
申请日：2021-05-20
Applicant: General Electric Company
Inventor： Joseph Zelina , Clayton S. Cooper , Michael T. Bucaro , Steven C. Vise , John Thomas Herbon
Abstract: A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.
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公开(公告)号：US20220373182A1
公开(公告)日：2022-11-24
申请号：US17327177
申请日：2021-05-21
Applicant: General Electric Company
Inventor： Hiranya Nath , Steven C. Vise , Michael A. Benjamin , Gurunath Gandikota
Abstract: A pilot fuel nozzle assembly includes a fuel nozzle, a swirler, and a vented pilot venturi. The vented pilot venturi has an annular wall with an oxidizer flow passage therein. An expansion flow surface portion of the venturi has a larger diameter at an outlet than at a throat of the venturi. A plurality of venturi oxidizer outlet ports extend through the expansion flow surface to the oxidizer flow passage within the annular wall to provide a flow of oxidizer through the venturi wall into a mixing cavity of the venturi and at an outlet end of the venturi. The oxidizer outlet ports are circumferentially spaced about a circumference of the expansion flow surface, and may be arranged in a plurality of rows. The oxidizer outlet ports may be angled with respect to the expansion flow surface and may angled circumferentially in a co-swirl direction with the swirler.
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公开(公告)号：US20220282627A1
公开(公告)日：2022-09-08
申请号：US17191566
申请日：2021-03-03
Applicant: General Electric Company
Inventor： Andrew Wickersham , Michael A. Benjamin , Steven C. Vise
Abstract: An engine may include an integrated diffuser-bleed baffle assembly, a diffuser, and a bleed port. The integrated diffuser-bleed baffle assembly fluidly coupled between the diffuser and the bleed port. The integrated diffuser-bleed baffle assembly is configured to flow a boundary layer flow from the diffuser to the bleed port. A baffle hole may be included in the integrated diffuser-bleed baffle assembly such that the assembly may function to dampen acoustic instabilities in the engine.
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公开(公告)号：US11428411B1
公开(公告)日：2022-08-30
申请号：US17323512
申请日：2021-05-18
Applicant: General Electric Company
Inventor： Sibtosh Pal , Clayton S. Cooper , Nicholas R. Overman , Steven C. Vise
Abstract: A venturi for a swirler assembly of a combustor for a gas turbine engine. The venturi has an annular wall having internal diameter of a forward end of the annular wall that is larger than an internal diameter of a middle portion of the annular wall, which is smaller than an internal diameter of an aft end of the annular wall. The internal surface of the annular wall has a plurality of grooves extending in a longitudinal direction from the forward end of the annular wall to the aft end of the annular wall. The plurality of grooves are angled with respect to a centerline axis of the annular wall and may be spiraled about the internal surface of the annular wall.
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