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公开(公告)号：US12092334B2
公开(公告)日：2024-09-17
申请号：US17307784
申请日：2021-05-04
Applicant: General Electric Company
Inventor： Narendra D. Joshi , Hendrik Pieter Jacobus de Bock , Richard L. Hart , Anil R. Duggal , Seung-Hyuck Hong
IPC: F23R3/40 , F02C3/20 , H01M8/04746 , F02C7/224
CPC classification number: F23R3/40 , F02C3/20 , H01M8/04761 , F02C7/224 , F05D2260/213 , F05D2260/232
Abstract: An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, the fuel cell stack configured (i) to direct fuel and air exhaust from the fuel cell stack into the combustor and (ii) to generate electrical energy, a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack, the catalytic partial oxidation convertor being configured to optimize a hydrogen content of a fuel stream to be directed into the fuel cell stack, and one or more subsystems electrically connected with the fuel cell stack, the one or more subsystems being configured to receive the electrical energy generated by the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine.
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公开(公告)号：US20220356847A1
公开(公告)日：2022-11-10
申请号：US17307780
申请日：2021-05-04
Applicant: General Electric Company
Inventor： Narendra D. Joshi , Hendrik Pieter Jacobus de Bock , Honggang Wang , Anil R. Duggal , Richard L. Hart , Seung-Hyuck Hong
IPC: F02C7/224 , F02C9/50 , F23R3/40 , F23R3/34 , H01M8/04701 , H01M8/04746
Abstract: An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, and a pre-burner system fluidly connected to the fuel cell stack. The fuel cell stack is configured to direct fuel and air exhaust from the fuel cell stack into the combustor. The pre-burner system is configured to control a temperature of an air flow directed into the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine. The engine assembly can further include a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack. The catalytic partial oxidation convertor is configured to develop a hydrogen rich fuel stream to be directed into the fuel cell stack.
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公开(公告)号：US11885498B2
公开(公告)日：2024-01-30
申请号：US17588876
申请日：2022-01-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra D. Joshi , Lawrence B. Kool , Joseph Zelina
Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.
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公开(公告)号：US20220344678A1
公开(公告)日：2022-10-27
申请号：US17240228
申请日：2021-04-26
Applicant: General Electric Company
Inventor： Hendrik Pieter Jacobus de Bock , Richard L. Hart , Honggang Wang , Narendra D. Joshi
IPC: H01M8/0258 , H01M8/0263
Abstract: A fuel cell unit that includes a support structure having a plurality of flow channels and an active layer membrane coupled with the support structure, the active layer membrane comprising at least one electrode layer. Each flow channel of the plurality of flow channels is configured to direct one of air and fuel across at least one electrode layer of an active layer membrane to create electric current. Each flow channel of the plurality of flow channels includes at least one enhancement feature that is configured to disrupt a formation of a boundary layer near a surface of the active layer membrane where reactions occur. The plurality of flow channels can be positioned in a zig-zag configuration to allow for an increase in power density of the fuel cell unit.
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公开(公告)号：US20190284943A1
公开(公告)日：2019-09-19
申请号：US15923545
申请日：2018-03-16
Applicant: General Electric Company
Inventor： Nicholas Joseph Kray , Paul Gerard Marsland , Wayne Allen Spence , Abhijeet Yadav , Samar Jyoti Kalita , Nitesh Jain , Narendra D. Joshi
Abstract: An airfoil for a turbomachinery rotor includes: a body having a first density, the body defining a pressure side and a suction side, the pressure side and suction side intersecting at a leading edge and a trailing edge; and a mass positioned within the body and having a second density, wherein the second density is greater than the first density, wherein the mass is offset from a center of gravity of the body in at least one axis.
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Patent Agency Ranking
公开(公告)号：US11923569B2
公开(公告)日：2024-03-05
申请号：US17240228
申请日：2021-04-26
Applicant: General Electric Company
Inventor： Hendrik Pieter Jacobus de Bock , Richard L. Hart , Honggang Wang , Narendra D. Joshi
IPC: H01M8/0258 , H01M8/0263
CPC classification number: H01M8/0258 , H01M8/0263 , H01M2250/20
Abstract: A fuel cell unit that includes a support structure having a plurality of flow channels and an active layer membrane coupled with the support structure, the active layer membrane comprising at least one electrode layer. Each flow channel of the plurality of flow channels is configured to direct one of air and fuel across at least one electrode layer of an active layer membrane to create electric current. Each flow channel of the plurality of flow channels includes at least one enhancement feature that is configured to disrupt a formation of a boundary layer near a surface of the active layer membrane where reactions occur. The plurality of flow channels can be positioned in a zig-zag configuration to allow for an increase in power density of the fuel cell unit.
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公开(公告)号：US20230243505A1
公开(公告)日：2023-08-03
申请号：US17588876
申请日：2022-01-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra D. Joshi , Lawrence B. Kool , Joseph Zelina
Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.
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公开(公告)号：US11578871B1
公开(公告)日：2023-02-14
申请号：US17587634
申请日：2022-01-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Narendra D. Joshi , Joseph Zelina
Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including: a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a primary fuel injector fluidly coupled to the dome inlet, and a second fuel injector fluidly coupled to the combustion chamber.
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公开(公告)号：US20220367890A1
公开(公告)日：2022-11-17
申请号：US17322507
申请日：2021-05-17
Applicant: General Electric Company
Inventor： Honggang Wang , Narendra D. Joshi , Hendrik Pieter Jacobus de Bock , Richard L. Hart
IPC: H01M8/04111 , H01M8/04828 , H01M8/04746 , H01M8/04014 , H01M8/04858 , H01M8/04701
Abstract: An engine assembly includes a combustor, a fuel cell stack fluidly connected to the combustor, the fuel cell stack being configured (i) to generate power using fuel and air directed into the fuel cell stack and (ii) to direct fuel and air exhaust from the fuel cell stack into the combustor, a compressor fluidly connected upstream of (i) the combustor and (ii) the fuel cell stack, the compressor being configured to generate compressed air to direct into the fuel cell stack, a turbine disposed downstream from the combustor, the turbine having a turbine inlet temperature, and a controller that is configured to control a power allocation between the fuel cell stack and the turbine based upon the turbine inlet temperature of the turbine. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that power the turbine.
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公开(公告)号：US20220349342A1
公开(公告)日：2022-11-03
申请号：US17244729
申请日：2021-04-29
Applicant: General Electric Company
Inventor： Manampathy G. Giridharan , Pradeep Naik , Narendra D. Joshi , Harris D. Abramson
Abstract: A fuel mixer configured to provide a fuel-air mixture to a combustor of an engine. The fuel mixer may include a mixer body having a mixer outer wall, a center body, an annular passageway defined between the mixer outer wall and the center body, and a fuel tube assembly placed circumferentially about the mixer body. The fuel tube assembly may include at least one fuel channel for injecting a fuel flow into the annular passageway. The fuel tube assembly may be configured to cool a boundary layer flow present in the annular passageway. The fuel tube assembly may be configured to cool the mixer outer wall, the center body, or both the mixer outer wall and the center body. Heat from the mixer outer wall, the center body, or both the mixer outer wall and the center body, may pass to the fuel flow in the fuel tube assembly.
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