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公开(公告)号：US11920479B2
公开(公告)日：2024-03-05
申请号：US16535256
申请日：2019-08-08
IPC分类号： F01D13/02 , B64C27/12 , B64D27/10 , B64D35/04 , F01D15/12 , F01D17/16 , F02C6/02 , F02C6/20 , F02C7/36 , F02C9/56
CPC分类号： F01D13/02 , B64C27/12 , B64D27/10 , B64D35/04 , F01D15/12 , F01D17/162 , F02C6/02 , F02C6/20 , F02C7/36 , F02C9/56 , F05D2220/329 , F05D2240/12 , F05D2240/60 , F05D2260/4031
摘要： A method of operating a multi-engine system of a rotorcraft includes, during a cruise flight segment of the rotorcraft, controlling a first engine to provide sufficient power and/or rotor speed demands of the cruise flight segment; and controlling a second engine to by providing a fuel flow to the second engine that is between 70% and 99.5% less than a fuel flow provided to the first engine. A turboshaft engine for a multi-engine system configured to drive a common load is also described.
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公开(公告)号：US11891960B2
公开(公告)日：2024-02-06
申请号：US17509694
申请日：2021-10-25
发明人： Seong Ik Park
CPC分类号： F02C9/56 , B64C29/00 , B64D2027/026
摘要： A powertrain control system is provided for a vertical take-off and landing aerial vehicle for urban air mobility. A powertrain of the vertical take-off and landing aerial vehicle is a hybrid type powertrain, in which the output shaft of a rotor driving motor is directly connected to a rotor, a battery is connected to the rotor driving motor to supply power thereto, and an engine and a generator are connected to a battery to charge and discharge the battery. The driving of the engine and the generator is controlled based on required power of the motor and the SOC of the battery in each flight step of the vertical take-off and landing aerial vehicle, and the SOC of the battery is constantly maintained at a predetermined level or higher.
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公开(公告)号：US20230332975A1
公开(公告)日：2023-10-19
申请号：US18213468
申请日：2023-06-23
IPC分类号： G01M3/28 , E21B43/26 , E21B34/08 , E21B43/267 , E21B47/12 , F02C7/22 , F02C9/28 , F02C9/56 , G01M3/26
CPC分类号： G01M3/2815 , E21B43/2607 , E21B34/08 , E21B43/267 , E21B47/12 , F02C7/222 , F02C9/28 , F02C9/56 , G01M3/26
摘要： Embodiments of systems and methods for supplying fuel, enabling communications, and conveying electric power associated with operation of a hydraulic fracturing unit of a plurality of hydraulic fracturing units are disclosed and may include a fuel line connection assembly configured to be connected to the first hydraulic fracturing unit and to supply fuel from a fuel source to a gas turbine engine connected to the hydraulic fracturing unit. A system also may include a communications cable assembly configured to be connected to the hydraulic fracturing unit and to enable data communications between the hydraulic fracturing unit and a data center or another hydraulic fracturing unit. A system further may include a power cable assembly configured to be connected to the hydraulic fracturing unit and to convey electric power between the hydraulic fracturing unit and a remote electrical power source or the plurality of hydraulic fracturing units.
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公开(公告)号：US11761846B2
公开(公告)日：2023-09-19
申请号：US17895757
申请日：2022-08-25
IPC分类号： G01M3/28 , E21B43/26 , E21B34/08 , E21B43/267 , E21B47/12 , F02C7/22 , F02C9/28 , F02C9/56 , G01M3/26
CPC分类号： G01M3/2815 , E21B34/08 , E21B43/2607 , E21B43/267 , E21B47/12 , F02C7/222 , F02C9/28 , F02C9/56 , G01M3/26
摘要： Embodiments of systems and methods for supplying fuel, enabling communications, and conveying electric power associated with operation of a hydraulic fracturing unit of a plurality of hydraulic fracturing units are disclosed and may include a fuel line connection assembly configured to be connected to the first hydraulic fracturing unit and to supply fuel from a fuel source to a gas turbine engine connected to the hydraulic fracturing unit. A system also may include a communications cable assembly configured to be connected to the hydraulic fracturing unit and to enable data communications between the hydraulic fracturing unit and a data center or another hydraulic fracturing unit. A system further may include a power cable assembly configured to be connected to the hydraulic fracturing unit and to convey electric power between the hydraulic fracturing unit and a remote electrical power source or the plurality of hydraulic fracturing units.
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公开(公告)号：US11753990B2
公开(公告)日：2023-09-12
申请号：US17864982
申请日：2022-07-14
摘要： A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.
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公开(公告)号：US09982607B2
公开(公告)日：2018-05-29
申请号：US15149256
申请日：2016-05-09
CPC分类号： F02C9/56 , F01D21/04 , F02C7/262 , F02C9/28 , F05D2270/02 , F05D2270/3015 , F05D2270/303
摘要： A method for use in a turbine control system includes controlling fuel supply to a gas turbine engine at least in part using a fuel supply limit determined as a first function of a rotational speed of a shaft of the gas turbine engine. The method also includes obtaining a first value representative of a rotational speed of the shaft, and differentiating the first value within a processing unit. The processing unit determines an adjusted fuel supply limit as an adjusted function of the first value. The adjusted function is based on the first function and the differentiated first value. The method further includes controlling the fuel supply to the gas turbine engine at least in part using the adjusted fuel supply limit.
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公开(公告)号：US20170292491A1
公开(公告)日：2017-10-12
申请号：US15518199
申请日：2015-10-06
发明人： Romain THIRIET , Jean-Michel BAZET , Guillaume COTTIN , Camel SERGHINE , Patrick MARCONI , Bertrand MOINE , Vincent POUMAREDE
CPC分类号： F02P7/028 , F01D19/00 , F02B53/12 , F02C7/232 , F02C7/264 , F02C9/266 , F02C9/56 , F02P5/045 , F05D2260/80 , Y02T50/671
摘要： A system for igniting a combustion chamber of a turboshaft engine, comprising: a plurality of start-up injectors which are suitable for injecting fuel into said chamber during a combustion-initiating phase; a circuit for supplying fuel to said start-up injectors, comprising a first sub-circuit, referred to as the primary start-up circuit, designed to supply fuel to some of said plurality of start-up injectors; a second sub-circuit, referred to as the secondary start-up circuit, designed to supply fuel to the other start-up injectors of said plurality.
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公开(公告)号：US20170101938A1
公开(公告)日：2017-04-13
申请号：US15128090
申请日：2015-03-20
CPC分类号： F02C9/56 , B64D31/06 , F02C3/10 , F02C9/46 , F02K3/12 , F05D2220/329 , F05D2270/091 , F05D2270/093 , F05D2270/095 , F05D2270/335 , Y02T50/671
摘要： The invention relates to a method for detecting a malfunction in a first turboshaft engine, referred to as an inoperative engine (4), of a twin-engine helicopter, and for controlling a second turboshaft engine, referred to as a healthy engine (5), each engine (4, 5) comprising protective stops regulated by a regulation device which define a maximum power regime, characterised in that it comprises: a step (10) of detecting an indication of failure of said inoperative engine (4); a step (11) of modifying said protective stops of said healthy engine (5) into protective stops which correspond to a maximum power single-engine regime, in the case of the detected indication of failure; a step (12) of confirming a failure of said inoperative engine (4); a step (13) of controlling an increase in the flow rate of fuel supply of said healthy engine (5), in the event of a confirmed failure.
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99.发明授权Device and a method of regulating a power plant including at least one turbine engine, and an aircraft 有权装置和调节包括至少一个涡轮发动机和飞行器的动力装置的方法公开(公告)号：US09404425B2
公开(公告)日：2016-08-02
申请号：US13747533
申请日：2013-01-23
申请人： AIRBUS HELICOPTERS
发明人： Laurent Martin
CPC分类号： F02C9/00 , F02C9/56 , F05D2220/329 , F05D2270/303 , F05D2270/304 , F05D2270/305
摘要： A regulator device (10) for regulating a turbine engine (3). The regulator device (10) includes mechanical power take-off means (100) for taking off power mechanically from a gas generator (4), and an engine computer (20) controlling said engine (3) to comply with at least a first limitation (LimTET, LimT45) of a temperature (TET, T45) of the gas within the engine, and with a second limitation (LimNg) of a speed of rotation (Ng) of the gas generator (4). The engine computer (20) determines whether the speed of rotation (Ng) of the gas generator has reached said second limitation (LimNg), and whether said temperature (TET, T45) has reached said first limitation (LimTET, LimT45). An avionics computer (30) causes the mechanical power take-off means (100) to operate if the speed of rotation (Ng) of the gas generator (4) has reached said second limitation (LimNg), and if said temperature (TET, T45) has not reached said first limitation (LimTET, LimT45).
摘要翻译： 一种用于调节涡轮发动机（3）的调节装置（10）。 调节装置（10）包括用于从气体发生器（4）机械地断电的机械动力输出装置（100）和控制所述发动机（3）的发动机计算机（20）至少符合第一限制 （LimTET，LimT45）和发动机内气体的温度（TET，T45）以及气体发生器（4）的旋转速度（Ng）的第二限制（LimNg）。 发动机计算机（20）确定气体发生器的旋转速度（Ng）是否已达到所述第二限制（LimNg），以及所述温度（TET，T45）是否达到所述第一限制（LimTET，LimT45）。 如果气体发生器（4）的旋转速度（Ng）达到第二限制（LimNg），则航空电子计算机（30）使得机械动力输出装置（100）运行，并且如果所述温度（TET， T45）尚未达到第一个限制（LimTET，LimT45）。
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100.发明申请APPLICATION OF PROBABILISTIC CONTROL IN GAS TURBINE TUNING WITH MEASUREMENT ERROR, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS 有权在测量误差的气体涡轮调谐中应用概率控制，相关控制系统，计算机程序产品和方法公开(公告)号：US20160138482A1
公开(公告)日：2016-05-19
申请号：US14546491
申请日：2014-11-18
IPC分类号： F02C9/56
CPC分类号： F02C9/56 , F02C9/28 , F02C9/42 , F05D2270/0831
摘要： Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and further adjusting an operating condition of each GT in the set of GTs based upon a determined emissions measurement error.
摘要翻译： 各种实施例包括一种系统，其具有：至少一个计算装置，其配置成通过执行动作来调节一组燃气轮机（GT），所述动作包括：基于每个所测量的环境条件，将所述GT组中的每个GT命令为基本负载水平 GT 指挥GT中的每个GT调整相应的输出以匹配标称兆瓦功率输出值，然后测量每个GT的实际排放值; 基于相应测量的实际发射值与环境条件下的标称发射值之间的差异来调整GT组中的每个GT的操作条件; 并且基于所确定的排放测量误差来进一步调整GT组中的每个GT的操作条件。
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