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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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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：US10823418B2
公开(公告)日：2020-11-03
申请号：US15447847
申请日：2017-03-02
Applicant: General Electric Company
Inventor： Joseph Zelina , Sarah Marie Monahan , Michael Anthony Benjamin , Venkat Eswarlu Tangirala , Sibtosh Pal , William Thomas Ross
Abstract: A combustor for a turbine engine includes an inner combustion liner and an outer combustion liner together defining at least in part an interior. The interior includes a combustion chamber and a main portion. The combustor also includes an inlet combustion liner at least partially defining the combustion chamber of the interior and including an inlet assembly. The inlet assembly includes at least two cavity air tubes arranged along the axial direction, each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air.
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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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45.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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Patent Agency Ranking
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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公开(公告)号：US20190120491A1
公开(公告)日：2019-04-25
申请号：US15793104
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. 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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公开(公告)号：US20180356099A1
公开(公告)日：2018-12-13
申请号：US15618326
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Joseph Zelina , Sibtosh Pal , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
CPC classification number: F23R3/56 , F01D9/041 , F02C5/02 , F02C7/222 , F05D2220/32 , F05D2240/35 , F23R3/286
Abstract: The present disclosure is directed to a propulsion system including a rotating detonation combustion (RDC) system defining a plurality of fuel-oxidizer mixing nozzles each defined by a converging-diverging nozzle wall defining a nozzle flowpath. The nozzle wall defines a throat and a lengthwise direction extended between a nozzle inlet and nozzle outlet along the lengthwise direction. The longitudinal centerline of the propulsion system and the radial direction together define a reference plane, and the lengthwise direction of the nozzle intersects the reference plane and defines a nozzle angle greater than zero degrees and approximately 80 degrees or less relative to the reference plane.
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公开(公告)号：US20180355795A1
公开(公告)日：2018-12-13
申请号：US15618575
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Sibtosh Pal , Joseph Zelina , Arthur Wesley Johnson , Clayton Stuart Cooper , Steven Clayton Vise
CPC classification number: F02C5/02 , F05D2240/35 , F23R3/28 , F23R3/42
Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system, the rotating detonation combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The rotating detonation combustion system includes an outer wall and an inner wall together defining at least in part a combustion chamber and a combustion chamber inlet; a nozzle located at the combustion chamber inlet defined by a nozzle wall, the nozzle defining a lengthwise direction and extending between a nozzle inlet and a nozzle outlet along the lengthwise direction, the nozzle inlet configured to receive a flow of oxidizer, the nozzle further defining a throat between the nozzle inlet and nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle, and wherein a diverging section of the nozzle wall defines a fluid diode; and a fuel injection port defining a fuel outlet located between the nozzle inlet and the nozzle outlet for providing fuel to the flow of oxidizer received through the nozzle inlet.
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公开(公告)号：US20180355793A1
公开(公告)日：2018-12-13
申请号：US15618682
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Joseph Zelina , Arthur Wesley Johnson , Clayton Stuart Cooper , Sibtosh Pal
Abstract: A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle. The hybrid combustion system further includes an inner liner extended generally along the longitudinal direction; an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction; a bulkhead wall disposed at the upstream end of the inner and outer liners, in which the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and a fuel manifold assembly extended at least partially through the bulkhead wall, in which the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber.
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