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公开(公告)号：US11268438B2
公开(公告)日：2022-03-08
申请号：US15705314
申请日：2017-09-15
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Allen Michael Danis , Jayanth Sekar , Pradeep Naik , Perumallu Vukanti , Arthur Wesley Johnson , Clayton Stuart Cooper , Karthikeyan Sampath
Abstract: An apparatus and method for a combustor, the combustor including combustor liner having a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and mixed with dilution air to form a flow of combustion gases. The flow of combustion gases travels through the combustor to a turbine section of an engine.
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62.发明授权公开(公告)号：US11131461B2
公开(公告)日：2021-09-28
申请号：US16700072
申请日：2019-12-02
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：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：US10935245B2
公开(公告)日：2021-03-02
申请号：US16196383
申请日：2018-11-20
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Manampathy Gangadharan Giridharan , Michael Anthony Benjamin , Pradeep Naik , Clayton Stuart Cooper , Vishal Sanjay Kediya
Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline. The centerbody further defines an annular centerbody groove or depression relative to the fuel nozzle centerline at a downstream end directly adjacent to a combustion chamber. The fuel nozzle further includes an inner sleeve extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline. The inner sleeve is positioned radially between the outer sleeve and the centerbody. The inner sleeve further defines an annular inner sleeve depression relative to the fuel nozzle centerline at the downstream end directly adjacent to the combustion chamber. The outer sleeve and the inner sleeve together define a first fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber. The inner sleeve and the centerbody together further define a second fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber.
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公开(公告)号：US10823422B2
公开(公告)日：2020-11-03
申请号：US15785726
申请日：2017-10-17
Applicant: General Electric Company
Inventor： Arthur Wesley Johnson , Joseph Zelina , Eric John Stevens , Clayton Stuart Cooper , Beverly Stephenson Duncan , Juntao Zhang
Abstract: A trapped vortex combustor for use in a gas turbine engine defines a radial direction, an axial direction, and a circumferential direction. The trapped vortex combustor includes an outer vortex chamber wall defining a forward end, and a dome attached to, or formed integrally with, the outer vortex chamber wall at the forward end of the outer vortex chamber wall. The dome and outer vortex chamber wall define at least in part a combustion chamber having an outer trapped vortex chamber. The dome includes an air chute defining an airflow direction. The radial direction and axial direction of the trapped vortex combustor define a reference plane extending through the air chute, the airflow direction of the air chute defining an angle greater than zero with the reference plane.
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Patent Agency Ranking
公开(公告)号：US20200158343A1
公开(公告)日：2020-05-21
申请号：US16196383
申请日：2018-11-20
Applicant: General Electric Company
Inventor： Gregory Allen Boardman , Manampathy Gangadharan Giridharan , Michael Anthony Benjamin , Pradeep Naik , Clayton Stuart Cooper , Vishal Sanjay Kediya
Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline. The centerbody further defines an annular centerbody groove or depression relative to the fuel nozzle centerline at a downstream end directly adjacent to a combustion chamber. The fuel nozzle further includes an inner sleeve extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline. The inner sleeve is positioned radially between the outer sleeve and the centerbody. The inner sleeve further defines an annular inner sleeve depression relative to the fuel nozzle centerline at the downstream end directly adjacent to the combustion chamber. The outer sleeve and the inner sleeve together define a first fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber. The inner sleeve and the centerbody together further define a second fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber.
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公开(公告)号：US20200088101A1
公开(公告)日：2020-03-19
申请号：US16675787
申请日：2019-11-06
Applicant: General Electric Company
Inventor： Joseph Zelina , Sibtosh Pal , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
Abstract: The present disclosure is directed to a propulsion system including a wall defining a combustion chamber inlet, a combustion chamber outlet, and a combustion chamber therebetween, a nozzle assembly disposed at the combustion chamber inlet, the nozzle assembly configured to provide a fuel/oxidizer mixture to the combustion chamber, a turbine nozzle coupled to the wall and positioned at the combustion chamber outlet, wherein the turbine nozzle defines a cooling circuit within the turbine nozzle, and a casing positioned radially adjacent to the wall, wherein a channel structure is positioned between the casing and the wall, the channel structure in fluid communication with the cooling circuit within the turbine nozzle, and wherein a flowpath is formed between the wall and the casing, the flowpath in fluid communication from the cooling circuit at the turbine nozzle to the nozzle assembly to provide a flow of oxidizer to the thereto.
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公开(公告)号：US20190264917A1
公开(公告)日：2019-08-29
申请号：US15904868
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 a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.
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公开(公告)号：US20190120493A1
公开(公告)日：2019-04-25
申请号：US15793129
申请日：2017-10-25
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, an annular inner wall extended at least partially along a lengthwise direction from the volute wall, and an annular outer wall extended at least partially along the lengthwise direction from the volute wall. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline and defines a combustion chamber within the volute wall. The inner wall and the outer wall are 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. A flow passage wall is extended to a portion of the volute wall and a portion of the outer wall. The flow passage wall defines a secondary flow passage and a tertiary flow passage between the volute wall, the outer wall, and the flow passage wall. The secondary flow passage and the tertiary flow passage are each in adjacent circumferential arrangement of one another around the combustor centerline. The volute wall and the outer wall together define one or more secondary outlet openings adjacent to the combustion chamber and in fluid communication with the combustion chamber. The outer wall defines one or more tertiary outlet openings in fluid communication with the tertiary flow passage and the primary flow passage.
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公开(公告)号：US20190086092A1
公开(公告)日：2019-03-21
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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