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公开(公告)号：US11598526B2
公开(公告)日：2023-03-07
申请号：US17232638
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Clayton Stuart Cooper , Allen M Danis
Abstract: A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline, each secondary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; and wherein the second vane angle is different from the first vane angle.
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公开(公告)号：US11408356B2
公开(公告)日：2022-08-09
申请号：US15723303
申请日：2017-10-03
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Duane Douglas Thomsen , Richard Wade Stickles , Clayton Stuart Cooper , Donald Lee Gardner , George ChiaChun Hsiao , Michael Anthony Benjamin , Shai Birmaher
Abstract: A system and method for operating a combustion system comprising a fuel nozzle defining at least one main fuel circuit and at least one pilot fuel circuit is generally provided. The method includes determining an overall flow of fuel, the overall flow of fuel defining a sum total fuel through the main fuel circuit and the pilot fuel circuit; determining a plurality of ranges of ratios of main fuel flow through the main fuel circuit versus pilot fuel flow through the pilot circuit from the overall flow of fuel, wherein each range of ratios is based on a combustion criterion different from one another; determining a resultant range of ratios of main fuel flow versus pilot fuel flow based on a hierarchy of combustion criteria, wherein the hierarchy of combustion criteria provides a priority ranking of the combustion criterion; and flowing the overall flow of fuel to the main fuel circuit and the pilot fuel circuit based on the resultant range of ratios of main fuel flow versus pilot fuel flow.
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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：US20210317990A1
公开(公告)日：2021-10-14
申请号：US17358377
申请日：2021-06-25
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Michael Anthony Benjamin , Clayton Stuart Cooper , Joseph Zelina , Eric John Stevens
Abstract: Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.
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公开(公告)号：US20210293412A1
公开(公告)日：2021-09-23
申请号：US17198150
申请日：2021-03-10
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Pradeep Naik , Joseph Zelina , Clayton Stuart Cooper
Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.
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Patent Agency Ranking
公开(公告)号：US11073286B2
公开(公告)日：2021-07-27
申请号：US15709958
申请日：2017-09-20
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Michael Anthony Benjamin , Clayton Stuart Cooper , Joseph Zelina , Eric John Stevens
Abstract: Various embodiments include a trapped vortex combustor and a method for operating trapped vortex combustor. In one embodiment, the trapped vortex combustor comprises a trapped vortex combustion zone and at least one secondary combustion zone disposed downstream of the trapped vortex combustion zone. The trapped vortex combustion zone is operable to receive and combust a first fuel and a first air and produce a first combustion product flowing toroidally therein. The at least one secondary combustion zone is operable to receive and combust the first combustion product and at least one second injection consisting of fuel and/or air and produce at least one second combustion product therein. The combustor may reduce the residence time of the highest temperature combustion products and achieve the lower NOx emission.
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公开(公告)号：US10890327B2
公开(公告)日：2021-01-12
申请号：US15896223
申请日：2018-02-14
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Hiranya Kumar Nath , Arvind Kumar Rao , Steven Clayton Vise , Perumallu Vukanti , Mayank Krisna Amble , Clayton Stuart Cooper
Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.
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公开(公告)号：US20200040843A1
公开(公告)日：2020-02-06
申请号：US16055313
申请日：2018-08-06
Applicant: General Electric Company
Inventor： Sibtosh Pal , Steven Clayton Vise , Arthur Wesley Johnson , Clayton Stuart Cooper , Joseph Zelina
Abstract: A ramjet engine and system and method for operation is generally provided. The ramjet includes a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines an inlet section, a combustion section, and an exhaust section. A fuel nozzle assembly is extended from the longitudinal wall. The fuel nozzle assembly defines a nozzle throat area. The fuel nozzle assembly is moveable along a radial direction to adjust the nozzle throat area based at least on a difference in pressure of a flow of fluid at an inlet of the inlet section and a pressure of the flow of fluid at the fuel nozzle assembly.
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49.发明授权公开(公告)号：US10520195B2
公开(公告)日：2019-12-31
申请号：US15618637
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Sibtosh Pal , Joseph Zelina , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
Abstract: A method and system of effervescent atomization of liquid fuel for a rotating detonation combustor (RDC) for a propulsion system is provided. The method includes flowing liquid fuel through a fuel injection port of a nozzle assembly of the RDC system; flowing a gas through the fuel injection port of the nozzle assembly volumetrically proportional to the liquid fuel; producing a gas-liquid fuel mixture at the fuel injection port by mixing the flow of gas and the flow of liquid fuel; flowing an oxidizer through a nozzle flowpath of the RDC system; producing an oxidizer-gas-liquid fuel mixture by mixing the gas-liquid fuel mixture and the flow of oxidizer within the nozzle flowpath; and igniting the oxidizer-gas-liquid fuel mixture within a combustion chamber of the RDC system.
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公开(公告)号：US20190264919A1
公开(公告)日：2019-08-29
申请号：US15904918
申请日：2018-02-26
Applicant: General Electric Company
Inventor： Sibtosh Pal , Steven Clayton Vise , Arthur Wesley Johnson , Clayton Stuart Cooper , Joseph Zelina
Abstract: A Brayton cycle engine including an inner wall assembly defining a detonation combustion region upstream thereof extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath. A method for operating the engine includes flowing an oxidizer through the gas flowpath; capturing a portion of the flow of oxidizer via the inner wall; flowing a first flow of fuel to the captured flow of oxidizer; producing a rotating detonation gases via a mixture of the first flow of fuel and the captured flow of oxidizer; flowing at least a portion of the detonation gases downstream to mix with the flow of oxidizer; flowing a second flow of fuel to the mixture of detonation gases and oxidizer; and burning the mixture of the second flow of fuel and the detonation gases/oxidizer mixture.
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