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公开(公告)号：US11280495B2
公开(公告)日：2022-03-22
申请号：US16808443
申请日：2020-03-04
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Steven Clayton Vise , Perumallu Vukanti , Mayank Krisna Amble , Clayton Stuart Cooper , Nicholas Ryan Overman , Karthikeyan Sampath , Allen Michael Danis , Craig Douglas Young
Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.
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公开(公告)号：US20180058696A1
公开(公告)日：2018-03-01
申请号：US15244797
申请日：2016-08-23
Applicant: General Electric Company
Inventor： Allen Michael Danis , Jagannath Ramchandra Nanduri , Nicholas Ryan Overman , Arthur Wesley Johnson , Sibtosh Pal
Abstract: A fuel-air mixer assembly that includes a mixer portion, and a flare cup portion coupled to the mixer portion. The flare cup portion includes a side wall that including an inlet opening and a discharge opening defined therein. The side wall is oriented such that the discharge opening is axi-asymmetrically shaped relative to a centerline of the fuel-air mixer assembly.
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Patent Agency Ranking
公开(公告)号：US20210278085A1
公开(公告)日：2021-09-09
申请号：US16808443
申请日：2020-03-04
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Steven Clayton Vise , Perumallu Vukanti , Mayank Krisna Amble , Clayton Stuart Cooper , Nicholas Ryan Overman , Karthikeyan Sampath , Allen Michael Danis , Craig Douglas Young
Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.
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公开(公告)号：US20230332549A1
公开(公告)日：2023-10-19
申请号：US17719659
申请日：2022-04-13
Applicant: General Electric Company
Inventor： Hejie Li , Michael A. Benjamin , Nicholas Ryan Overman
CPC classification number: F02C9/28 , F02C7/224 , F05D2240/35 , F05D2270/303 , F05D2270/20 , F05D2220/323 , F05D2270/301
Abstract: A fuel temperature control system and a method of controlling a fuel temperature for a turbine engine including supplying an aviation fuel to a fuel nozzle fluidly coupled to a combustion chamber. A fuel temperature sensor for determining at least one input parameter to define an inlet fuel temperature of the aviation fuel in the fuel nozzle. A controller for receiving the at least one input parameter and for calculating a calculated flow number in the fuel nozzle. The controller capable of comparing the calculated flow number and a reference flow number associated with a threshold during a steady state condition to determine if the aviation fuel is boiling inside the fuel nozzle.
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5.发明申请公开(公告)号：US20190056114A1
公开(公告)日：2019-02-21
申请号：US15681875
申请日：2017-08-21
Applicant: General Electric Company
Inventor： Allen Michael Danis , Scott Matthew Bush , Arthur Wesley Johnson , Nicholas Ryan Overman , Kent Hamilton Lyle , Eric John Stevens
Abstract: The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.
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公开(公告)号：US12012903B2
公开(公告)日：2024-06-18
申请号：US17719659
申请日：2022-04-13
Applicant: General Electric Company
Inventor： Hejie Li , Michael A. Benjamin , Nicholas Ryan Overman
CPC classification number: F02C9/28 , F02C7/224 , F05D2220/323 , F05D2240/35 , F05D2270/20 , F05D2270/301 , F05D2270/303
Abstract: A fuel temperature control system and a method of controlling a fuel temperature for a turbine engine including supplying an aviation fuel to a fuel nozzle fluidly coupled to a combustion chamber. A fuel temperature sensor for determining at least one input parameter to define an inlet fuel temperature of the aviation fuel in the fuel nozzle. A controller for receiving the at least one input parameter and for calculating a calculated flow number in the fuel nozzle. The controller capable of comparing the calculated flow number and a reference flow number associated with a threshold during a steady state condition to determine if the aviation fuel is boiling inside the fuel nozzle.
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7.发明授权公开(公告)号：US11181274B2
公开(公告)日：2021-11-23
申请号：US15681875
申请日：2017-08-21
Applicant: General Electric Company
Inventor： Allen Michael Danis , Scott Matthew Bush , Arthur Wesley Johnson , Nicholas Ryan Overman , Kent Hamilton Lyle , Eric John Stevens
IPC: F23R3/36 , F02C9/40 , F23R3/28 , F02C7/22 , F02C3/20 , F02C3/06 , F02C7/228 , F23R3/34 , F02C9/28
Abstract: The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.
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