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公开(公告)号：EP2835517B1
公开(公告)日：2018-06-20
申请号：EP14179020.4
申请日：2014-07-29
CPC分类号： F02C7/00 , F02C7/047 , F05D2260/231 , F05D2270/311 , F05D2270/312 , F05D2270/313 , Y02T50/675
摘要： A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.
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2.发明公开Base load estimation for a combined cycle power plant with steam turbine clutch 有权Abschätzungder Maximallastfürein Kombikraftwerk mit Dampfturbenenkupplung
公开(公告)号：EP2835505A1
公开(公告)日：2015-02-11
申请号：EP14179076.6
申请日：2014-07-30
发明人： Chen, Yuhui
CPC分类号： G01L25/00 , F01D15/10 , F01K5/02 , F02C6/18 , F02C9/00 , F05D2220/64 , F05D2220/72 , F05D2220/76 , F05D2260/4023 , F05D2260/821 , F05D2270/312 , F05D2270/313 , F05D2270/331 , F05D2270/335 , Y02E20/16
摘要： Systems and methods for estimating a base load in a combined cycle power plant with a steam turbine clutch (160) are provided. According to one embodiment of the disclosure, a system (100) may include a controller (700) and a processor (750) communicatively coupled to the controller (700). The processor (750) may be configured to receive operating parameters associated with a combined cycle power plant. The combined cycle power plant may comprise a gas turbine (110) permanently coupled to a generator (130) and a steam turbine (120) selectively coupled to the generator (130) via a clutch (160). The processor (750) may be further configured to receive an engagement status associated with the clutch (160) and receive first data and second data. Based on the engagement status, the processor (750) may select the first data or the second data and use that to estimate a base load. The base load estimation may be calibrated based on the operating parameters.
摘要翻译： 提供了一种用于估计具有蒸汽轮机离合器（160）的联合循环发电厂中的基本负载的系统和方法。 根据本公开的一个实施例，系统（100）可以包括通信地耦合到控制器（700）的控制器（700）和处理器（750）。 处理器（750）可以被配置为接收与组合循环发电厂相关联的操作参数。 联合循环发电厂可以包括永久地联接到发电机（130）的燃气轮机（110）和经由离合器（160）选择性地联接到发电机（130）的蒸汽轮机（120）。 处理器（750）可以被进一步配置成接收与离合器（160）相关联的接合状态并接收第一数据和第二数据。 基于参与状态，处理器（750）可以选择第一数据或第二数据，并使用它来估计基本负载。 可以基于操作参数来校准基本负载估计。
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公开(公告)号：EP3255282A1
公开(公告)日：2017-12-13
申请号：EP17173662.2
申请日：2017-05-31
CPC分类号： F02C9/18 , F01D17/145 , F01D25/24 , F02C3/04 , F02K3/06 , F04D27/0215 , F04D27/0223 , F04D27/023 , F04D29/325 , F04D29/522 , F05D2220/323 , F05D2240/35 , F05D2260/52 , F05D2260/606 , F05D2260/85 , F05D2270/312 , F05D2270/65 , F16K1/126 , F16K31/1221
摘要： A valve includes a housing with a mounting portion (66), a venting portion (72), and a cap portion (76). The valve also includes a piston (60) in the housing with a shaft (86), a disc (88), and a flange (90), the piston being moveable between a closed position and an open position. The valve also includes a vessel (62) that is in contact with the cap portion and the flange wherein fluid pressure contained in the vessel biases the piston into one of the opened position and the closed position.
摘要翻译： 阀包括具有安装部分（66），通气部分（72）和盖部分（76）的外壳。 该阀还包括壳体中的具有轴（86），圆盘（88）和凸缘（90）的活塞（60），活塞可在关闭位置和打开位置之间移动。 阀还包括与盖部分和凸缘接触的容器（62），其中包含在容器中的流体压力将活塞偏置到打开位置和关闭位置中的一个。
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公开(公告)号：EP3242007A1
公开(公告)日：2017-11-08
申请号：EP17168550.6
申请日：2017-04-27
CPC分类号： G01M15/14 , F01K23/101 , F02C9/50 , F02D41/0007 , F02D41/1401 , F02D2041/1412 , F02D2041/1433 , F02D2200/0402 , F02D2200/0414 , F02D2200/0418 , F02D2200/703 , F02D2250/18 , F02M25/022 , F05D2220/32 , F05D2260/207 , F05D2260/211 , F05D2260/212 , F05D2270/053 , F05D2270/304 , F05D2270/306 , F05D2270/311 , F05D2270/312 , F05D2270/313 , F05D2270/335 , F05D2270/44 , F05D2270/71 , Y02E20/16
摘要： A system 10 includes an engine 14 configured to generate power to drive a load 32. The system also includes a power augmentation system 16 configured to augment a power output of the engine when the power augmentation system is activated. Additionally, the system includes a controller 12 operatively coupled to the power augmentation system. The controller is configured to estimate a potential change in the power output of the engine caused by activation of the power augmentation system using a power augmentation model and an engine performance model.
摘要翻译： 系统10包括配置成产生动力以驱动负载32的发动机14.该系统还包括配置成在动力增强系统被激活时增大发动机的动力输出的动力增强系统16。 另外，该系统包括可操作地耦合到功率增强系统的控制器12。 控制器被配置为使用功率增大模型和发动机性能模型来估计由功率增大系统的激活引起的发动机功率输出中的潜在变化。
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5.发明公开PROCEDE ET DISPOSITIF D'AJUSTEMENT D'UNE VALEUR DE CONSIGNE D'UN PARAMETRE INFLUENCANT UNE POUSSEE D'UN MOTEUR A TURBINE A GAZ 审中-公开用来设置参数的参考值的方法和装置到燃气涡轮发动机的BOOSTING的影响
公开(公告)号：EP2864616A1
公开(公告)日：2015-04-29
申请号：EP13731411.8
申请日：2013-06-11
申请人： SNECMA
CPC分类号： F02C9/44 , F02C9/28 , F05D2270/051 , F05D2270/3011 , F05D2270/303 , F05D2270/304 , F05D2270/312 , F05D2270/313 , F05D2270/708
摘要： The method of adjusting a reference value of at least one parameter that influences the thrust of a gas turbine engine powering an aircraft during a phase of flight of this aircraft comprises: — a step (E20) of obtaining a current value of at least one operating variable (T2, Pamb) of the engine; — a step (E50) of extracting from a preestablished table (T) a decrement value (ΔXN2,ΔPRS2) for said at least one parameter associated with the current value of said at least one engine operating variable; and — a step (E60) of adjusting the reference value of said at least one parameter by applying to it the decrement value taken from the table.
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6.发明公开
公开(公告)号：EP3287625A1
公开(公告)日：2018-02-28
申请号：EP17184600.9
申请日：2017-08-03
发明人： MOECKLY, Kevin , LING, Richard , MORRIS, David
CPC分类号： F04D27/0246 , F02C9/52 , F02C9/54 , F04D27/001 , F04D29/563 , F05D2220/50 , F05D2270/101 , F05D2270/3011 , F05D2270/303 , F05D2270/312 , F05D2270/313
摘要： A compressor surge avoidance control system and method for a gas turbine engine includes sensing a plurality of engine inlet parameters, and receiving a fuel command value. The sensed parameters are processed to determine a surge fuel value that is representative of a fuel flow above which, for the sensed engine inlet parameters, a compressor surge will likely occur. The surge fuel value and the fuel command value are compared, and a protective action signal is generated if the fuel command value exceeds the surge fuel value.
摘要翻译： 一种用于燃气涡轮发动机的压缩机喘振避免控制系统和方法包括感测多个发动机进气参数并接收燃料命令值。 处理所感测的参数以确定表示燃料流量的喘振燃料值，在所述燃料流量以上，对于所感测的发动机入口参数，压缩机喘振可能发生。 比较浪涌燃料值和燃料指令值，并且如果燃料指令值超过喘振燃料值，则产生保护动作信号。
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公开(公告)号：EP2860375B1
公开(公告)日：2017-04-05
申请号：EP14184758.2
申请日：2014-09-15
申请人： Rolls-Royce plc
发明人： Swann, Peter
CPC分类号： F02C9/28 , F02C3/20 , F02C7/22 , F02C9/26 , F02C9/40 , F05D2270/08 , F05D2270/311 , F05D2270/312 , F05D2270/313 , Y02T50/671 , Y02T50/677
摘要： This invention concerns a method of delivering fuel to an aircraft engine 60, which involves providing a plurality of distinct fuel sources 20, 22, a first fuel source 20 comprising a first fuel having a first aromatic content and a second fuel source 22 comprising a second fuel having a second aromatic content. One or more ambient atmospheric condition is determined for at least a portion of a flight path of the aircraft, said condition being indicative of a likelihood of contrail 135 formation by the engine 60. A desirous fuel composition for combustion by the engine is determined based upon the one or more ambient atmospheric condition and a ratio of the first and second fuels from said respective fuel sources is selected according to said desirous fuel composition. The selected ratio of the first and second fuels is delivered to the aircraft engine 60.
摘要翻译： 本发明涉及将燃料输送到飞行器发动机60的方法，该方法包括提供多个不同的燃料源20,22，第一燃料源20，其包括具有第一芳烃含量的第一燃料和包含第二燃料源22的第二燃料源22， 燃料具有第二芳烃含量。 为飞行器的飞行路径的至少一部分确定一个或多个环境大气条件，所述条件指示发动机60形成转向135的可能性。由发动机燃烧的期望的燃料组合物基于 所述一个或多个环境大气条件以及来自所述各个燃料源的第一和第二燃料的比例根据所述希望的燃料组成来选择。 所选择的第一和第二燃料的比例被输送到飞机发动机60。
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公开(公告)号：EP2860375A1
公开(公告)日：2015-04-15
申请号：EP14184758.2
申请日：2014-09-15
申请人： Rolls-Royce plc
发明人： Swann, Peter
CPC分类号： F02C9/28 , F02C3/20 , F02C7/22 , F02C9/26 , F02C9/40 , F05D2270/08 , F05D2270/311 , F05D2270/312 , F05D2270/313 , Y02T50/671 , Y02T50/677
摘要： This invention concerns a method of delivering fuel to an aircraft engine 60, which involves providing a plurality of distinct fuel sources 20, 22, a first fuel source 20 comprising a first fuel having a first aromatic content and a second fuel source 22 comprising a second fuel having a second aromatic content. One or more ambient atmospheric condition is determined for at least a portion of a flight path of the aircraft, said condition being indicative of a likelihood of contrail 135 formation by the engine 60. A desirous fuel composition for combustion by the engine is determined based upon the one or more ambient atmospheric condition and a ratio of the first and second fuels from said respective fuel sources is selected according to said desirous fuel composition. The selected ratio of the first and second fuels is delivered to the aircraft engine 60.
摘要翻译： 本发明涉及一种向飞机发动机60输送燃料的方法，该方法包括提供多个不同的燃料源20,22，包括具有第一芳香族成分的第一燃料的第一燃料源20和具有第二燃料源的第二燃料源22 具有第二芳族含量的燃料。 针对飞机的飞行路线的至少一部分确定一个或多个环境大气条件，所述条件指示发动机60形成的轨迹的可能性。用于由发动机燃烧的期望燃料成分基于 根据所述期望燃料成分来选择所述一个或多个环境大气条件以及来自所述相应燃料源的第一燃料和第二燃料的比率。 第一燃料和第二燃料的所选比率被传递到飞机发动机60。
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公开(公告)号：EP3296522A1
公开(公告)日：2018-03-21
申请号：EP17182126.7
申请日：2017-07-19
CPC分类号： B64D31/12 , B64D41/00 , B64F1/34 , F01D13/00 , F01D19/00 , F01D21/003 , F02C6/00 , F02C6/20 , F02C7/277 , F05D2220/323 , F05D2270/13 , F05D2270/304 , F05D2270/312 , F05D2270/54
摘要： A system is provided for cross engine coordination during gas turbine engine motoring. The system includes a first gas turbine engine (10A) of a first engine system (100A), a first air turbine starter (120A) of the first engine system (100A), a first starter air valve (116A) of the first engine system (100A), and a controller (102A). The controller (102A) is operable to command the first starter air valve (116A) to control delivery of compressed air to the first air turbine starter (120A) during motoring of the first gas turbine engine (10A), monitor cross engine data of a second gas turbine engine (10B) of a second engine system (100B) to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve (116A), and command an adjustment to the first engine system (100A) to compensate for the modified aspect of the compressed air based on the cross engine data.
摘要翻译： 在燃气轮机发动机驱动期间提供用于交叉引擎协调的系统。 该系统包括第一发动机系统（100A）的第一燃气涡轮发动机（10A），第一发动机系统（100A）的第一空气涡轮起动器（120A），第一发动机系统（100A）的第一起动器空气阀（116A） （100A）和控制器（102A）。 控制器（102A）可操作以命令第一启动器空气阀（116A）在第一燃气涡轮发动机（10A）的驱动期间控制压缩空气向第一空气涡轮启动器（120A）的输送，监测第一燃气涡轮发动机 第二发动机系统（100B）的第二燃气涡轮发动机（10B），以检测修改在第一启动器空气阀（116A）接收的压缩空气的一个方面的当前状况或命令动作，并且命令对第一启动器空气阀 发动机系统（100A）基于交叉引擎数据补偿压缩空气的修改方面。
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公开(公告)号：EP3063380A1
公开(公告)日：2016-09-07
申请号：EP14861158.5
申请日：2014-10-29
CPC分类号： F02C7/20 , F01D5/146 , F01D17/08 , F01D21/003 , F01D25/162 , F05D2240/126 , F05D2250/71 , F05D2260/607 , F05D2270/20 , F05D2270/3061 , F05D2270/312 , F05D2270/313 , F05D2270/80 , Y02T50/673 , Y02T50/675 , Y10T29/49229
摘要： An engine strut (100) for providing fan hub frame structural support and monitoring an air flow (116) within an aircraft engine (100) includes an airfoil (120) coupled to the aircraft engine (100) and has a first portion (122) and a second portion (124). The first portion (122) is positioned upstream of the second portion (124) with respect to the air flow. A shield (126) is coupled to the engine (100) and positioned between the first portion (122) and the second portion (124). The shield (126) includes a first side (128) spaced from the first portion (122) and defining a first flow path (164) with the first portion (122). The shield further (126) includes a second side (130) spaced from the second portion (124) and defining a second flow path (169) with the second portion (124). At least one sensor (182) is coupled to the aircraft engine (100) and positioned in flow communication with the second flow path (169).
摘要翻译： 用于提供风扇轮毂框架结构支撑和监测飞行器发动机内的空气流的发动机支柱包括联接到飞行器发动机的翼型件并且具有第一部分和第二部分。 第一部分相对于空气流定位在第二部分的上游。 屏蔽件联接到发动机并且定位在第一部分和第二部分之间。 屏蔽包括与第一部分间隔开并且限定具有第一部分的第一流动路径的第一侧。 屏蔽还包括与第二部分间隔开并与第二部分限定第二流路的第二侧。 至少一个传感器耦合到飞行器引擎并且与第二流动路径流动连通地定位。
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