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公开(公告)号：US11846423B2
公开(公告)日：2023-12-19
申请号：US17232691
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Clayton Stuart Cooper , Michael Anthony Benjamin , Hiranya Kumar Nath , Rameshkumar Muthuvel Chandrasekaran
IPC: F23R3/28 , F02M61/18 , B01F23/21 , B01F25/10 , B01F23/213 , B01F101/00
CPC classification number: F23R3/286 , B01F23/2132 , B01F25/10 , F02M61/18 , B01F2101/503
Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.
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公开(公告)号：US11804607B2
公开(公告)日：2023-10-31
申请号：US17581229
申请日：2022-01-21
Applicant: General Electric Company
Inventor： Honggang Wang , Michael Anthony Benjamin , Seung-Hyuck Hong , Richard L. Hart
IPC: H01M8/04 , H01M8/04007 , H01M8/04303 , H01M8/04746 , B64D31/00 , B64D27/24 , B64D27/10 , B64D27/02 , H01M8/10
CPC classification number: H01M8/04007 , B64D27/10 , B64D27/24 , B64D31/00 , H01M8/04303 , H01M8/04753 , B64D2027/026 , H01M8/10 , H01M2250/20
Abstract: A method for operating a propulsion system for an aircraft, the propulsion system including a gas turbine engine and a fuel cell assembly, the fuel cell assembly including a fuel cell stack having a solid oxide fuel cell defining an outlet positioned to remove output products from the solid oxide fuel cell during operation, the method including: operating the fuel cell assembly to provide output products to a combustor of a combustion section of the gas turbine engine; and operating the fuel cell assembly, the gas turbine engine, or both such that a pressure within an anode of the solid oxide fuel cell is less than a pressure within a cathode of the solid oxide fuel cell, is less than a pressure within a combustion chamber of the gas turbine engine, or both while operating the gas turbine engine.
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公开(公告)号：US11794912B2
公开(公告)日：2023-10-24
申请号：US17568254
申请日：2022-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Michael Anthony Benjamin
IPC: B64D27/10 , H01M8/04111 , H01M8/04746 , H01M8/04992 , H01M8/04701 , F02C9/00 , B64D27/02
CPC classification number: B64D27/10 , F02C9/00 , H01M8/04111 , H01M8/04738 , H01M8/04776 , H01M8/04992 , B64D2027/026 , H01M2250/20
Abstract: A gas turbine engine includes a fuel cell assembly including a fuel cell stack and defining a fuel cell assembly operating parameter, a fuel source, and a turbomachine. The turbomachine includes a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel from the fuel source and further configured to receive output products from the fuel cell stack. A controller is configured to perform operations including receiving data indicative of system operation conditions, determining a set of fuel cell operating conditions to move the system emission output into or maintain the system emission output within an emissions range, and controlling the fuel cell assembly operating parameter according to the determined set of fuel cell operating conditions.
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公开(公告)号：US20230278714A1
公开(公告)日：2023-09-07
申请号：US17684677
申请日：2022-03-02
Applicant: General Electric Company
Inventor： Honggang Wang , Michael Anthony Benjamin
IPC: B64D27/24 , H01M8/2475 , H01M8/248 , B64D27/10 , F02C9/44
CPC classification number: B64D27/24 , H01M8/2475 , H01M8/248 , B64D27/10 , F02C9/44 , H01M2250/20 , B64D2027/026
Abstract: An anti-stall system for an aircraft may be provided, where the aircraft includes a propulsion system including a fuel cell assembly and a combustion engine, the combustion engine including a compressor section having a compressor. The anti-stall system may include at least one sensor configured to sense data indicative of at least one operating parameter indicative of a compressor stall condition of the compressor; and a controller including a processor and a memory storing instructions that when executed by the processor cause the controller to determine that the at least one operating parameter has achieved a compressor stall condition threshold and execute an anti-stall action responsive to determining that the at least one operating parameter has achieved the compression stall condition threshold. The anti-stall action may be configured to adjust at least one fuel cell parameter.
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公开(公告)号：US11725817B2
公开(公告)日：2023-08-15
申请号：US17363088
申请日：2021-06-30
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Rajendra Mahadeorao Wankhade , Daniel J. Kirtley , Michael Anthony Benjamin
CPC classification number: F23R3/08 , F01D9/023 , F23R3/002 , F23R3/06 , F23R3/60 , F02C7/28 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F23R3/005
Abstract: A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.
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Patent Agency Ranking
公开(公告)号：US20230238552A1
公开(公告)日：2023-07-27
申请号：US17581197
申请日：2022-01-21
Applicant: General Electric Company
Inventor： Honggang Wang , Michael Anthony Benjamin , Seung-Hyuck Hong , Richard L. Hart
IPC: H01M8/04111 , H01M4/86 , H01M8/0432 , H01M8/04791 , F02C7/22
CPC classification number: H01M8/04111 , H01M4/8652 , H01M8/04343 , H01M8/04798 , F02C7/22 , H01M2250/20 , H01M2008/1293
Abstract: A method for operating a fuel cell assembly, the fuel cell assembly including a fuel cell stack having a solid oxide fuel cell, the solid oxide fuel cell having an anode, a cathode, and an electrolyte, the method including: determining a temperature setpoint for the fuel cell stack, for output products of the fuel cell stack, or both; and controlling a volume of oxidant provided to the anode in response to the determined temperature setpoint to control a temperature of the fuel cell stack, a temperature of the output products of the fuel cell stack, or both.
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27.发明公开公开(公告)号：US20230228221A1
公开(公告)日：2023-07-20
申请号：US17568359
申请日：2022-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Michael Anthony Benjamin
CPC classification number: F02C9/40 , F02C7/22 , F23R3/36 , F05D2220/32 , F05D2240/35
Abstract: Systems and methods including a plurality of reformer stacks extended around the combustion chamber. The reformer stacks are distributed along a length of the combustion chamber in the axial direction and configured to provide output products to the combustion chamber.
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公开(公告)号：US20230212988A1
公开(公告)日：2023-07-06
申请号：US17568099
申请日：2022-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Michael Anthony Benjamin
IPC: B64D31/00 , B64D27/24 , H01M8/04701 , H01M8/04858 , B64D37/00 , B64D27/10 , B60L58/30 , B64D27/02
CPC classification number: B64D31/00 , B64D27/24 , H01M8/04701 , H01M8/04895 , B64D37/00 , H01M8/04925 , B64D27/10 , B60L58/30 , B64D2027/026 , H01M2250/20 , B60L2200/10
Abstract: A propulsion system for an aircraft includes a fuel cell assembly, the fuel cell assembly including a fuel cell, and a turbomachine, the turbomachine including a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel and further configured to receive output products from the fuel cell. A controller is configured to receive data indicative of an engine constraint of the turbomachine, determine that the engine constraint has achieved a fuel cell trim threshold; and perform a fuel cell corrective action with the fuel cell assembly in response to determining that the engine constraint has achieved the fuel cell trim threshold.
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公开(公告)号：US11561008B2
公开(公告)日：2023-01-24
申请号：US15684083
申请日：2017-08-23
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , Randall Charles Boehm , Michael Anthony Benjamin , Beverly Stephenson Duncan , Jeffrey Lyal Powell
Abstract: Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.
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公开(公告)号：US20220333782A1
公开(公告)日：2022-10-20
申请号：US17232691
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Steven Clayton Vise , Clayton Stuart Cooper , Michael Anthony Benjamin , Hiranya Kumar Nath , Rameshkumar Muthuvel Chandrasekaran
Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.
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