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公开(公告)号：US12050440B2
公开(公告)日：2024-07-30
申请号：US17598003
申请日：2020-03-11
CPC分类号： G05B13/0265 , F02C9/00 , F05D2220/72 , F05D2270/082 , F05D2270/11 , F05D2270/44
摘要： Method and device for controlling a machine in accordance with to multiple control objectives in which machine control is based on automated learning of subordinate control skills, wherein the device provides multiple subordinate control skills which are each assigned to a different one of the multiple control objectives, the device provides multiple learning processes that are reinforcement learning processes that are each assigned to a different one of the multiple control objectives and are configured to optimize the corresponding subordinate control skill based on input data received from the machine, and where the device is configured to determine a superordinate control skill based on the subordinate control skills and to control the machine based on the superordinate control skill.
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公开(公告)号：US12012231B2
公开(公告)日：2024-06-18
申请号：US17593785
申请日：2020-03-16
CPC分类号： B64F5/60 , B64D45/00 , F02C6/20 , B64D2045/0085 , F05D2270/11 , F05D2270/44
摘要： The invention relates to a method for monitoring at least one aircraft engine, said method including an acquisition (100) according to the first and second sets of measurements of respectively endogenous and exogenous variables. The method also includes:
a normalization (200) of the measurements of the first set relative to the measurements of the second set,
a generation (300) of a current model representative of the evolution of the behavior of the engine based on the normalized measurements,
a detection (400) of potential abnormality in the behavior of the engine based on a comparison of the current model with a reference model,
a generation (500) of a maintenance message,
a transmission (600) of said ground message,
the acquisition, normalization, generation of a current model, the detection and generation of a maintenance message being made on board the aircraft.-
公开(公告)号：US11746708B2
公开(公告)日：2023-09-05
申请号：US17940288
申请日：2022-09-08
CPC分类号： F02C9/00 , G06F8/65 , H04W12/06 , F05D2270/44 , F05D2270/54
摘要： A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine. The communication adapter also includes a memory system and processing circuitry configured to receive one or more configuration items from the offboard system, confirm an authentication between the communication adapter and the engine control, apply a cryptographic algorithm using one or more parameters received and cryptographic information to decrypt the one or more configuration items, wherein the cryptographic information includes a combination of received cryptographic information and previously stored cryptographic information, and transfer the one or more configuration items to the engine control based on the authentication.
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公开(公告)号：US11655823B2
公开(公告)日：2023-05-23
申请号：US16955977
申请日：2017-12-20
发明人： Edward A. Fowler
CPC分类号： F04D15/0066 , F04D1/06 , G05B13/00 , G05B17/00 , G06F30/20 , F04B2203/0209 , F05D2260/81 , F05D2270/335 , F05D2270/44 , G06F2111/10
摘要： A method and controller for operating a pumping station. The method includes receiving (1102), by at least one controller (910, 952), sensor data (712) of a first pumping station (900) corresponding to a liquid being transported from the first pumping station (900). The method includes predicting (1104) arrival of the liquid, by the at least one controller (910, 952), at a second pumping station (900). The method includes executing (1106) one or more pump models (720), by the at least one controller (910, 952), according to the sensor data (712) to determine an optimal pumping configuration. The method includes operating (1108) one more pumps of the second pumping station (900), by the at least one controller (910, 952), according to the optimal pumping configuration.
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公开(公告)号：US11649045B2
公开(公告)日：2023-05-16
申请号：US17949511
申请日：2022-09-21
IPC分类号： B64C27/12 , B64D31/00 , F02C6/20 , F02C9/56 , F02C9/44 , F02C9/48 , F02C9/42 , B64D27/14 , B64D31/06 , F02C9/28 , B64C27/06 , B64D27/24 , B64D27/02 , B64D35/08
CPC分类号： B64C27/12 , B64D27/14 , B64D31/00 , B64D31/06 , F02C6/206 , F02C9/28 , F02C9/42 , F02C9/44 , F02C9/48 , F02C9/56 , B64C27/06 , B64D27/24 , B64D35/08 , B64D2027/026 , F05D2220/329 , F05D2270/13 , F05D2270/44
摘要： A power management system for a multi engine rotorcraft having a main rotor system with a main rotor speed. The power management system includes a first engine that provides a first power input to the main rotor system. A second engine selectively provides a second power input to the main rotor system. The second engine has at least a zero power input state and a positive power input state. A power anticipation system is configured to provide the first engine with a power adjustment signal in anticipation of a power input state change of the second engine during flight. The power adjustment signal causes the first engine to adjust the first power input to maintain the main rotor speed within a predetermined rotor speed threshold range during the power input state change of the second engine.
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公开(公告)号：US20190234860A1
公开(公告)日：2019-08-01
申请号：US15884804
申请日：2018-01-31
发明人： Maurice Jean , Frederic Busnel
CPC分类号： G01N15/10 , F01M11/10 , F02C9/00 , F02D41/1401 , F02D2041/1412 , F05D2260/80 , F05D2260/82 , F05D2270/44 , G01M15/14 , G01N15/0205 , G01N15/0227 , G01N33/2888 , G01N2015/0053 , G01N2015/0294 , G01N2015/1087 , G01N2015/1093 , G01N2015/1493 , G01N2015/1497
摘要： Systems and methods for predicting engine performance are provided herein. A fluid sample having particles suspended therein is received from a first engine. A plurality of particles are extracted from the fluid sample. Features of the plurality of particles extracted from the fluid sample and features of particles of reference fluid samples from a plurality of reference engines are obtained. A plurality of correlation indices indicative of a level of correlation between the first engine and each one of the plurality of reference engines is determined. The correlation indices are compared to a threshold to determine a subset of the plurality of reference engines. Performance history for the engines in the subset is obtained. From the performance history, the first engine is determined as having a similarity in performance with the engines in the subset. An output is generated indicating a predicted performance for the first engine.
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公开(公告)号：US20180187608A1
公开(公告)日：2018-07-05
申请号：US15450882
申请日：2017-03-06
CPC分类号： F02C9/26 , F02C9/00 , F05D2220/32 , F05D2260/81 , F05D2270/3011 , F05D2270/303 , F05D2270/312 , F05D2270/313 , F05D2270/44 , F05D2270/54 , F05D2270/706 , F05D2270/71 , G05B13/04 , G05B17/02
摘要： A method includes obtaining a steady state model that models a process controlled by a controller of a gas turbine. The steady state model estimates at least one output of the process based on at least one input. The method includes creating a transient model by perturbing at least one input of the steady state model to estimate the at least one output, the at least one output comprising transient characteristics of the gas turbine. The method includes adjusting a gain of the controller continuously, at predetermined intervals, or based on a requirement trigger, or any combination thereof, based on the transient model. The gain defines a response to a difference between a reference signal and a feedback signal of the controller of the gas turbine. The method includes sending the adjusted gain to the controller. The controller controls the process based on the adjusted gain.
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公开(公告)号：US10006315B2
公开(公告)日：2018-06-26
申请号：US14229625
申请日：2014-03-28
发明人： Brett Matthew Thompson , Michael Joseph Alexander , Matthew John Mosley , Steven Di Palma , Paul Jeffrey Mitchell , Justin Aaron Allen , Kihyung Kim
CPC分类号： F01K23/101 , F01K23/18 , F02C6/00 , F02C6/18 , F02C7/057 , F02C9/48 , F02C9/50 , F05D2220/32 , F05D2220/72 , F05D2270/303 , F05D2270/3032 , F05D2270/331 , F05D2270/44 , G05B15/02 , Y02E20/16
摘要： Systems, methods, and tangible non-transitory machine readable medium are provided. A system includes a gas turbine system configured to produce power by combusting a fuel. The system further includes a controller configured to control the gas turbine system via an operating 2-dimensional surface area and a setpoint, wherein the operating 2-dimensional surface area comprises a plurality of limits defining bounds for the operating 2-dimensional surface area, and wherein the setpoint is configured to be disposed inside the operating 2-dimentionsal surface area or on the limits.
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公开(公告)号：US20180163639A1
公开(公告)日：2018-06-14
申请号：US15378264
申请日：2016-12-14
发明人： Yimin Huang , Hua Zhang , Timothy Andrew Healy , Iris Z. Hu
CPC分类号： F02C9/52 , F02C3/04 , F02C7/08 , F02C7/228 , F02C9/00 , F02C9/54 , F05D2260/80 , F05D2260/81 , F05D2260/821 , F05D2270/44
摘要： A system and a method for predicting and optimizing remaining hardware life of gas turbine components. Operating parameters of the gas turbine which may impact remaining hardware life are sensed and tracked using a plurality of sensors in communication with a control system including a computing device. Remaining hardware life is predicted using a physics-based hardware lifing model. The hardware lifing model may include an output of a filtration model configured to monitor contaminants based on a pressure drop across a filter. Optimizing the remaining hardware life is achieved by the control system adjusting one or more operation settings of the gas turbine.
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公开(公告)号：US20180038238A1
公开(公告)日：2018-02-08
申请号：US15228664
申请日：2016-08-04
CPC分类号： F01D11/20 , F01D5/12 , F01D11/22 , F01D17/02 , F01D21/003 , F05D2220/32 , F05D2240/11 , F05D2240/307 , F05D2270/44 , F05D2270/62 , F05D2270/66 , F05D2270/80 , F05D2270/821 , Y02T50/671
摘要： Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring a blade clearance of a first secondary BOAS that is circumferentially adjacent the first primary BOAS based on a position of the first primary BOAS when the blade clearance of the first primary BOAS is at the first predetermined blade clearance, determining if the measured blade clearance of the first secondary BOAS is at a value corresponding to the first predetermined blade clearance, and adjusting the position of the first secondary BOAS when the blade clearance of the first secondary BOAS is not at the first predetermined blade clearance with an actuator operably connected to the first secondary BOAS.
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