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公开(公告)号：US12130016B1
公开(公告)日：2024-10-29
申请号：US18326647
申请日：2023-05-31
Applicant: General Electric Company
Inventor： Hiranya Nath , Clayton S. Cooper , Steven C. Vise , Michael A. Benjamin , Pradeep Naik , Ranganatha Narasimha Chiranthan , Perumallu Vukanti , Sibtosh Pal
Abstract: A combustor for a turbine engine includes a main combustion chamber, an annular dome, and a secondary combustion chamber positioned downstream of the annular dome. A plurality of first mixing assemblies are disposed through the annular dome and include a pilot mixer. The pilot mixer injects a pilot mixer fuel-air mixture axially into the main combustion chamber and generates a first recirculation zone within the main combustion chamber. A plurality of second mixing assemblies are disposed at the secondary combustion chamber axially aft of the first mixing assemblies and include a main mixer. The main mixer injects a main mixer fuel-air mixture into the secondary combustion chamber to produce combustion gases and to generate a second recirculation zone within the secondary combustion chamber axially aft of the first recirculation zone. The secondary combustion chamber injects the combustion gases into the main combustion chamber.
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公开(公告)号：US11473780B2
公开(公告)日：2022-10-18
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：US20220290864A1
公开(公告)日：2022-09-15
申请号：US17658750
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Sibtosh Pal , Steven Clayton Vise , Athur Wesley Johnson , Clayton Stuart Cooper , Josep 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：US11359578B2
公开(公告)日：2022-06-14
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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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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Patent Agency Ranking
6.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：US12169068B2
公开(公告)日：2024-12-17
申请号：US17819399
申请日：2022-08-12
Applicant: General Electric Company
Inventor： Joseph Zelina , Shai Birmaher , Sibtosh Pal , Clayton S. Cooper
Abstract: A combustor for a turbine engine. The combustor includes a fuel injector and a fluid injection system in fluid communication with the combustor. The fuel injector includes a mixer assembly with a pilot mixer and a main mixer. The pilot mixer and the main mixer operate during high power operation of the turbine engine. The fluid injection system injects a fluid into the combustor during high power operation of the turbine engine. The fluid is shut off during low power operation of the turbine engine and during mid-level power operation of the turbine engine.
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公开(公告)号：US20240287952A1
公开(公告)日：2024-08-29
申请号：US18643376
申请日：2024-04-23
Applicant: General Electric Company
Inventor： Sibtosh Pal , Steven Clayton Vise , Arthur Wesley Johnson , Clayton Stuart Cooper , Joseph Zelina
CPC classification number: F02K7/10 , F02K7/02 , F02K7/08 , F02K7/16 , F23R7/00 , F05D2220/10 , F05D2250/90 , F23R3/18 , F23R3/34
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：US20240280264A1
公开(公告)日：2024-08-22
申请号：US18296220
申请日：2023-04-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bhavya Naidu Panduri , Perumallu Vukanti , Pradeep Naik , Michael T. Bucaro , Sibtosh Pal , Aritra Chakraborty , Pabitra Badhuk , Arijit Sinha Roy , Ajoy Patra , R Narasimha Chiranthan
IPC: F23R3/00
Abstract: A combustor for a gas turbine engine. The combustor having a dome wall, a set of fuel cups, an inner liner, an outer liner, and a set of dilution passages. The dome wall, the inner liner, and the outer liner, together, at least partially defining a combustion chamber. The set of dilution passages terminating in a plurality of dilution holes arranged in a dilution hole arrangement provided in at least one of the inner liner or the outer liner. The dilution hole arrangement having at least a first subset of dilution holes arranged along a first leg and a second subset of dilution holes arranged along a second leg.
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公开(公告)号：US12060995B1
公开(公告)日：2024-08-13
申请号：US18187773
申请日：2023-03-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Aritra Chakraborty , Perumallu Vukanti , Pradeep Naik , Arijit Sinha Roy , Bhavya Naidu Panduri , R Narasimha Chiranthan , Ajoy Patra , Michael T. Bucaro , Sibtosh Pal , Pabitra Badhuk
IPC: F23R3/06
CPC classification number: F23R3/06
Abstract: A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.
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