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公开(公告)号：US20190264920A1
公开(公告)日：2019-08-29
申请号：US15904991
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 and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.
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公开(公告)号：US10393383B2
公开(公告)日：2019-08-27
申请号：US15067926
申请日：2016-03-11
Inventor： Philip H Snyder
Abstract: A wave rotor combustor for use in a gas turbine engine includes an inlet assembly, a rotor drum, and an outlet assembly. The inlet assembly is arranged to direct a flow of gasses into rotor passages formed in the rotor drum. The rotor drum is arranged to receive the gasses. The outlet assembly is arranged to direct the gasses out of the rotor drum.
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公开(公告)号：US10221763B2
公开(公告)日：2019-03-05
申请号：US15390105
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Andrew Maxwell Peter , Kapil Kumar Singh , Keith Robert McManus , Joel Haynes , Anthony Dean
IPC: F02C5/02 , F02C3/16 , F02C7/264 , F23R7/00 , F02C3/04 , F02K7/08 , F02K7/075 , F02C5/10 , F02C5/00 , F02C3/14 , F23R3/34 , F23R3/42 , F23R3/28 , F23R3/56
Abstract: A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.
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4.发明申请公开(公告)号：US20180356096A1
公开(公告)日：2018-12-13
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：US12234773B1
公开(公告)日：2025-02-25
申请号：US18098575
申请日：2023-01-18
Applicant: HySonic Technologies, LLC
Inventor： Zachary Rauch , Carlo Scalo
Abstract: Rotating Detonation Combustors (RDCs)—or Rotating Detonation Engines (RDEs)—are special propulsion devices that generate thrust by burning a fuel-oxidizer mixture via a rotating detonation wave, rather than a traditional flame. RDCs may exhibit unwanted secondary acoustic disturbances that negatively affect their detonative operation. Suppressing such unwanted/secondary acoustic modes associated with the main detonation wave may be achieved by an acoustically absorptive lining mountable in the internal walls of a RDC.
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Patent Agency Ranking
公开(公告)号：US10527287B2
公开(公告)日：2020-01-07
申请号：US16092694
申请日：2017-04-06
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Guillaume Taliercio , Nicolas Savary , Olivier Lamaison
Abstract: An injector for a gas turbine combustion chamber, includes a fluid feed system; an injector body extending along a longitudinal axis; an injection head arranged on the injector body and configured to spray the fluid in a direction that is inclined relative to the longitudinal axis; and an actuator configured to turn the injector selectively about the longitudinal axis so as to vary the direction in which the fluid is sprayed; wherein the actuator is configured to enable the orientation of the injector to be varied by turning about the longitudinal axis through an amplitude less than or equal to 90°.
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公开(公告)号：US10443493B2
公开(公告)日：2019-10-15
申请号：US15041191
申请日：2016-02-11
Inventor： Calvin W. Emmerson , Philip H. Snyder
Abstract: A wave rotor assembly includes a wave rotor combustor and an exit duct. The wave rotor combustor includes an aft plate formed to include an exit port and a rotor drum mounted for rotation relative to the aft plate. The rotor drum is formed to include a plurality of rotor passages arranged to align with the exit port during rotation of the rotor drum. The exit duct is coupled to the aft plate and defines a passage arranged to receive exhaust gasses flowing through the exit port.
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公开(公告)号：US20190264918A1
公开(公告)日：2019-08-29
申请号：US15904892
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. A strut is extended through the gas flowpath between the longitudinal walls. An inner wall assembly is extended from the longitudinal wall and the strut into the gas flowpath. The inner wall assembly and strut together define a plurality of detonation combustion regions in the gas flowpath upstream of the inner wall assembly.
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公开(公告)号：US20190242582A1
公开(公告)日：2019-08-08
申请号：US15890637
申请日：2018-02-07
Applicant: General Electric Company
Inventor： Arthur Wesley Johnson , Steven Clayton Vise , Clayton Stuart Cooper , Joseph Zelina , Sibtosh Pal
CPC classification number: F23R3/56 , F02C3/04 , F05D2220/32 , F05D2240/35 , F23R3/04 , F23R3/286 , F23R2900/03042
Abstract: A rotating detonation combustion (RDC) system including a detonation chamber wall extended along a longitudinal direction. The detonation chamber wall defines a detonation chamber radially in between the detonation chamber walls. The RDC system further includes a fuel-oxidizer nozzle defining a first convergent-divergent nozzle disposed upstream of the detonation chamber, and a gas nozzle defining a second convergent-divergent nozzle extended through the detonation chamber wall at least partially along the longitudinal direction. The gas nozzle provides a flow of gas into the detonation chamber at least partially co-directional to the detonation chamber wall.
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公开(公告)号：US09933164B2
公开(公告)日：2018-04-03
申请号：US15120015
申请日：2015-01-27
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Nicolas Savary , Patrick Berteau , Bernard Carrere , Jean-Marc Dubourdieu , Ludovic Naudot
IPC: F23R3/52 , F23R3/58 , F02C7/20 , F23R3/50 , F23R3/54 , F23R3/28 , F23R3/42 , F23R3/48 , F23C5/02 , F23R3/46 , F23R3/56 , F23R3/60 , F23D11/10 , F23R3/00
CPC classification number: F23R3/52 , F02C7/20 , F05D2230/50 , F05D2230/51 , F05D2230/64 , F05D2230/642 , F05D2240/35 , F05D2240/90 , F05D2260/30 , F23C5/02 , F23D11/103 , F23R3/002 , F23R3/007 , F23R3/28 , F23R3/283 , F23R3/42 , F23R3/425 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/54 , F23R3/56 , F23R3/58 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019
Abstract: An annular combustion chamber (10) for a turbomachine (100), the combustion chamber presenting an axial direction (X), a radial direction, and an azimuth direction, and comprising a first annular wall (12) and a second annular wall (14), each wall delimiting at least a portion of the volume of the annular combustion chamber (10), the first and second walls (12, 14) presenting complementary fitting elements (12d, 14d), the first wall (12) presenting at least one first through hole (12f), while the second wall (14) presents at least one second through hole (14f), the combustion chamber (10) also having at least one pin (18) engaged in a pair of holes comprising a first hole (12f) and a second hole (14f), said pin (18) locking the fitting of the first and second walls (12, 14).
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