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公开(公告)号：US12030657B1
公开(公告)日：2024-07-09
申请号：US18496117
申请日：2023-10-27
申请人： RTX CORPORATION
发明人： Yasir Al-Nadawi , Milos Ilak , Pratyush Kumar
CPC分类号： B64D31/00 , F01D15/10 , B64D27/026 , F05D2270/053 , F05D2270/31 , F05D2270/709
摘要： A method for a hybrid electric propulsion (HEP) system includes utilizing a soft actor-critic agent, which includes at least one neural network, and a control barrier function (CBF) filter to obtain a power splitting profile for an HEP system. The power splitting profile includes an electric motor power for an electric motor of the HEP system and a gas turbine power for a gas turbine of the HEP system. The electric motor power and gas turbine power collectively provide a combined HEP output power. The method also includes, during a flight of an aircraft that includes the HEP system, performing an output action for the HEP system based on the power splitting profile. The utilizing is performed based on a predefined fuel consumption objective and a state of charge of at least one battery that powers the electric motor. A system for a HEP system is also disclosed.
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公开(公告)号：US11859542B2
公开(公告)日：2024-01-02
申请号：US17645162
申请日：2021-12-20
发明人： Richard K Keller , Paul Johnson
CPC分类号： F02C6/04 , F02C9/18 , F02K3/025 , F05D2220/90 , F05D2240/128 , F05D2260/606 , F05D2270/053 , F05D2270/335
摘要： A system including a turbine engine configured to generate rotor power and produce an engine air flow. The system is configured to provide rotor power to one of more shaft-driven lift fans to generate a first thrust on an aircraft body and provide a gas flow to one or more gas-driven lift fans to generate a second thrust on the aircraft body. The gas flow may be at least a portion of the engine air flow produced by the turbine engine. The turbine engine may be configured to exhaust another portion of the engine air flow through a jet nozzle to generate an engine thrust. In examples, the system includes at least a second turbine engine. The one of more shaft-driven lift fans and/or one of more gas-driven lift fans be powered by the turbine engine, the second turbine engine, or both the turbine engine and the second turbine engine.
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公开(公告)号：US20230383673A1
公开(公告)日：2023-11-30
申请号：US17828837
申请日：2022-05-31
CPC分类号： F01D21/003 , F02C9/18 , F05D2260/606 , F05D2260/83 , F05D2270/053 , F05D2270/3013 , F05D2270/304 , F05D2270/305 , F05D2270/313 , F05D2270/71
摘要： A method for checking a closing point for a bleed-off valve for a gas turbine engine includes determining a modulation characteristic curve for the bleed-off valve, determining a nominal closing point value for the bleed-off valve on the modulation characteristic curve, operating the gas turbine engine and increasing an engine power of the gas turbine engine until the gas turbine engine parameter reaches a predetermined testing value, and determining a bleed-off valve measured value and a gas turbine engine measured value when the gas turbine engine parameter reaches the predetermined testing value. The gas turbine engine measured value is different than the nominal closing point value. The method further includes determining an extrapolated closing point value and checking the closing point for the bleed-off valve by comparing the bleed-off valve measured value or the gas turbine engine measured value to the extrapolated closing point value.
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公开(公告)号：US11739696B2
公开(公告)日：2023-08-29
申请号：US17548786
申请日：2021-12-13
发明人： Michel Labrecque , Kevin Nguyen , Ninad Joshi
CPC分类号： F02C9/16 , F02C3/04 , F05D2220/30 , F05D2240/35 , F05D2270/053 , F05D2270/303 , F05D2270/3013
摘要： A method and a system for synthesizing output power provided by an engine are provided. The engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the engine, a pressure of fluid at an exit of the compressor section, a temperature upstream of the exit of the compressor section, and a fuel flow rate to the engine are determined. A synthesized value of output power provided by the engine is determined based on a product of at least a first factor, a second factor, and a third factor, the first factor being a function of the pressure, the second factor being a function of the temperature, and the third factor being a function of the fuel flow rate. The synthesized value of output power provided by the engine is output.
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公开(公告)号：US20230258135A1
公开(公告)日：2023-08-17
申请号：US18162949
申请日：2023-02-01
申请人： ROLLS-ROYCE plc
发明人： Peter SWANN
CPC分类号： F02C9/40 , F02C7/22 , F05D2220/323 , F05D2270/053 , F05D2270/08 , F05D2270/303
摘要： A system has first and second fuel stores for first and second fuels, an engine, a fuel distribution system, first and second flow rates of the fuel contributing to a total flow rate of fuel; and a controller for controlling the relative fractions of the total flow rate of fuel to the engine according to the required power output of the engine such that the relative fraction of the total flow rate of fuel to the engine represented by the second flow rate increases with increasing required power output of the engine. The fuels are selected such that using only the second fuel results in a lower engine temperature than using only the first fuel, for the same mechanical power and/or the second fuel has a lower specific energy than the first and/or the second fuel produces more water during combustion than the first fuel per unit of fuel energy.
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公开(公告)号：US20230182909A1
公开(公告)日：2023-06-15
申请号：US18103935
申请日：2023-01-31
CPC分类号： B64D27/24 , B64D27/10 , F01D15/10 , F02C6/14 , F02C7/36 , H02K7/1823 , F05D2270/053 , B64D2221/00 , F02C3/107
摘要： An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US20190061969A1
公开(公告)日：2019-02-28
申请号：US16110699
申请日：2018-08-23
CPC分类号： B64D31/06 , F01D17/105 , F01D17/16 , F02C9/20 , F02C9/54 , F04D27/0246 , F05D2220/323 , F05D2270/03 , F05D2270/053 , F05D2270/061 , F05D2270/304 , F05D2270/309 , F05D2270/54
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A power level difference between a requested engine power level and a current engine power level is determined at a computing device. The power level difference is compared to a predetermined power threshold at the computing device. When the power level difference exceeds the predetermined power threshold, a position control signal for changing a position of the variable geometry mechanism is generated and output at the computing device, the position control signal generated based on a requisite bias level, the requisite bias level being based on the power level difference.
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公开(公告)号：US20180156127A1
公开(公告)日：2018-06-07
申请号：US15576962
申请日：2016-04-20
发明人： Kai Hausmann , Carsten Seiler , Dirk Wall
CPC分类号： F02C7/228 , F02C9/26 , F02C9/28 , F05D2270/053 , F05D2270/10 , F05D2270/14 , F05D2270/303 , F05D2270/309 , F05D2270/335 , F05D2270/701 , F05D2270/708 , F23N2025/08 , F23N2041/20
摘要： An operating method for a gas turbine by partial-load operation, includes setting of a power setpoint value for a predefined temperature value; determining the two operating curves as a function of temperature according to the power of the gas turbine, wherein the power setpoint value is located between said operating curves; determining the difference in power of said two operating curves at the substantially constant predetermined temperature value; determining a power deviation from the predetermined power setpoint value of one of the two operating curves at the substantially constant predetermined temperature value; calculating an interpolated operating curve deviation on the basis of the difference in power and the power deviation, wherein the temperature is a turbine outlet temperature or a computationally determined turbine inlet temperature.
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公开(公告)号：US09945264B2
公开(公告)日：2018-04-17
申请号：US14587682
申请日：2014-12-31
发明人： Lisa Anne Wichmann , Achalesh Kumar Pandey , Eric Thomas Pool , Christopher Michael Raczynski , Suresh Pamujula
IPC分类号： G05D3/12 , G05D5/00 , G05D9/00 , G05D11/00 , G05D17/00 , F01K13/02 , G05B13/04 , F01K23/10 , F02C6/00 , G05F1/66 , F02C9/28
CPC分类号： F01K13/02 , F01K23/101 , F02C6/00 , F02C9/28 , F05D2220/32 , F05D2220/72 , F05D2260/80 , F05D2270/053 , F05D2270/709 , G05B13/04 , G05F1/66 , Y02E20/16
摘要： A control method for optimizing or enhancing an operation of a power plant that includes thermal generating units for generating electricity. The power plant may include multiple possible operating modes differentiated by characteristics of operating parameters. The method may include tuning a power plant model so to configure a tuned power plant model. The method may further include simulating proposed operating modes of the power plant with the tuned power plant model. The simulating may include a simulation procedure that includes: defining a second operating period; selecting the proposed operating modes from the possible operating modes; with the tuned power plant model, performing a simulation run for each of the proposed operating modes whereby the operation of the power plant during the second operating period is simulated; and obtaining simulation results from each of the simulation runs.
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公开(公告)号：US09879615B2
公开(公告)日：2018-01-30
申请号：US14971716
申请日：2015-12-16
发明人： Lewis Berkley Davis, Jr. , Scott Arthur Day , Timothy Andrew Healy , Harold Lamar Jordan, Jr. , Rex Allen Morgan
CPC分类号： F02C9/42 , F02C9/00 , F05D2220/32 , F05D2240/40 , F05D2270/053 , F05D2270/08 , F05D2270/335 , F05D2270/71 , G05B13/048
摘要： A system includes: a computing device configured to tune a set of gas turbines (GTs) by: commanding each GT to a base load level; commanding each GT to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; updating a pre-existing emissions model for each GT based upon the adjusted operating condition; running a set of operating conditions on each GT and measuring an updated emissions value; and refining the updated pre-existing emissions model based upon a difference between the updated emissions value and the updated pre-existing emissions model.
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