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公开(公告)号：US20240167416A1
公开(公告)日：2024-05-23
申请号：US18280231
申请日：2021-05-25
申请人： TURBOGEN LTD.
发明人： David LIOR
摘要： A reconfigurable hybrid solar gas turbine system includes a turbocharger (TC), a gas turbine engine, and a solar energy module. The TC and engine each include a compressor and a turbine joined by a turboshaft. The engine further includes a burner, a mixer, a generator, and a flow control valve. The system operates in a semi-open cycle in which the TC receives inlet ambient air. The burner receives pressurized air from the TC and fuel, for example from an NG source. The mixer combines hot gas flows from both the burner and the solar energy module to form a combined flow, whose mixing ratio is determined by a position of the flow control valve, thereby reconfiguring the system in response to variations in incident solar irradiance. Electrical power is generated by the engine generator and an optional TC generator. The engine and/or solar energy module may include a recuperator.
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公开(公告)号：US11892167B2
公开(公告)日：2024-02-06
申请号：US17791232
申请日：2021-01-07
申请人： Turbogen Ltd.
发明人： Michael Levitsky
摘要： An atomizer provides a high-quality fuel-air mixture to a gas turbine engine, by combining air input from an engine compressor and fuel input from a single low-pressure fuel supply pump. The atomizer includes an atomizer body, a main vortex chamber, a secondary vortex chamber for improving quality of the fuel-air mixture, and a fuel sleeve providing fuel to the secondary vortex chamber. The main vortex chamber includes a main outlet nozzle in fluid communication with a combustion chamber inlet of the gas turbine engine. The secondary vortex chamber includes a secondary outlet nozzle in fluid communication with the main vortex chamber. The fuel sleeve has a blind channel with a longitudinal axis and a fuel tip. The same atomizer may be used for startup mode and for all operational modes of the gas turbine engine.
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公开(公告)号：US11725579B2
公开(公告)日：2023-08-15
申请号：US17430347
申请日：2020-02-12
申请人： Turbogen Ltd.
发明人： David Lior
摘要： A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.
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公开(公告)号：US20220136458A1
公开(公告)日：2022-05-05
申请号：US17433251
申请日：2020-02-24
申请人： Turbogen Ltd.
发明人： David LIOR
摘要： A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.
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公开(公告)号：US20220128002A1
公开(公告)日：2022-04-28
申请号：US17430347
申请日：2020-02-12
申请人： Turbogen Ltd.
发明人： David LIOR
摘要： A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.
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公开(公告)号：US11846202B2
公开(公告)日：2023-12-19
申请号：US17433251
申请日：2020-02-24
申请人： Turbogen Ltd.
发明人： David Lior
CPC分类号： F01D5/046 , F02K3/02 , F04D29/584
摘要： A method for cooling a high-temperature radial gas turbine engine increases turbine thermal efficiency and/or extends turbine operational lifetime. A bleed flow path enables cooling air to flow from a compressor outlet and along surfaces of the gas turbine rotors. The amount of cooling increases in proportion to a bleed fraction, which is defined as the ratio of mass flow in the bleed flow path to total mass flow in the compressor outlet. The heated air in the bleed flow path is mixed with the main mass flow into the turbine engine, so as to restore mass flow into the turbine, while maintaining a high turbine operating temperature and thermal efficiency. The thermal efficiency of a recuperator also increases in proportion to the bleed fraction.
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公开(公告)号：US11815021B2
公开(公告)日：2023-11-14
申请号：US17797464
申请日：2021-02-02
申请人： Turbogen Ltd.
发明人： David Lior
CPC分类号： F02C7/18 , F02C6/18 , F02C7/22 , F05D2260/213 , F05D2260/232
摘要： A compact cooling and boosting gas turbine system provides combined cooling, heating, and electrical power with high energy efficiency. The system has a pressure booster and a turbo-compressor. The pressure booster includes a fuel inlet, a fuel outlet, and a piston, and is in fluid communication with a gas turbine engine. The pressure booster also includes a coolant inlet, a coolant chamber, and a coolant outlet, and is in fluid communication with a closed pressurized coolant flow. The turbo-compressor includes a compressor and a turbine, and is in fluid communication with a water input flow and with the closed pressurized coolant flow. A coolant flow control valve controls the closed pressurized coolant flow. The system is configured to provide a cold water flow for a first position of the flow control valve and to provide a hot water flow for a second position of the flow control valve.
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公开(公告)号：US20220412261A1
公开(公告)日：2022-12-29
申请号：US17797464
申请日：2021-02-02
申请人： Turbogen Ltd.
发明人： David LIOR
摘要： A compact cooling and boosting gas turbine system provides combined cooling, heating, and electrical power with high energy efficiency. The system has a pressure booster and a turbo-compressor. The pressure booster includes a fuel inlet, a fuel outlet, and a piston, and is in fluid communication with a gas turbine engine. The pressure booster also includes a coolant inlet, a coolant chamber, and a coolant outlet, and is in fluid communication with a closed pressurized coolant flow. The turbo-compressor includes a compressor and a turbine, and is in fluid communication with a water input flow and with the closed pressurized coolant flow. A coolant flow control valve controls the closed pressurized coolant flow. The system is configured to provide a cold water flow for a first position of the flow control valve and to provide a hot water flow for a second position of the flow control valve.
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公开(公告)号：US20220364731A1
公开(公告)日：2022-11-17
申请号：US17791232
申请日：2021-01-07
申请人： Turbogen Ltd.
发明人： Michael LEVITSKY
摘要： An atomizer provides a high-quality fuel-air mixture to a gas turbine engine, by combining air input from an engine compressor and fuel input from a single low-pressure fuel supply pump. The atomizer includes an atomizer body, a main vortex chamber, a secondary vortex chamber for improving quality of the fuel-air mixture, and a fuel sleeve providing fuel to the secondary vortex chamber. The main vortex chamber includes a main outlet nozzle in fluid communication with a combustion chamber inlet of the gas turbine engine. The secondary vortex chamber includes a secondary outlet nozzle in fluid communication with the main vortex chamber. The fuel sleeve has a blind channel with a longitudinal axis and a fuel tip. The same atomizer may be used for startup mode and for all operational modes of the gas turbine engine.
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