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1. 发明公开

EP3258067A1 DETECTING COMBUSTION ANOMALIES IN GAS TURBINES USING AUDIO OUTPUT 审中-公开
标题翻译：利用音频输出检测燃气轮机燃烧异常
公开(公告)号：EP3258067A1
公开(公告)日：2017-12-20
申请号：EP17174732.2
申请日：2017-06-07
申请人： General Electric Company
发明人： FULLER, Jason Dean , CROTHERS, Sarah Lori , SOPCIC, Paige Marie , FLAVIN, Daniel Joseph
IPC分类号： F01D17/08 , F01D21/00
CPC分类号： F23N5/16 , F01D17/08 , F01D21/00 , F01D21/003 , F05D2240/35 , F05D2270/083 , F05D2270/80 , F05D2270/81 , F23N2023/08 , F23N2025/04 , F23N2037/00 , F23R3/46 , G01M15/14
摘要： In one embodiment, a turbine system (10) includes a combustion system (20) comprising a plurality of combustion cans (23), a number of sensors (22), each of the number of sensors (22) coupled to a respective combustion can (23) of the number of combustion cans (23), and a controller (24). The controller (24) includes a memory (26, 27) storing one or more processor-executable routines and a processor (28, 29) configured to access and execute the one or more routines encoded by the memory (26, 27). The one or more routines, when executed cause the processor (28, 29) to receive one or more signals from the number of sensors (22), convert the one or more signals to audio output (34), and output the converted audio output (34) via one or more audio output devices (30, 31).
摘要翻译：在一个实施例中，涡轮机系统（10）包括燃烧系统（20），其包括多个燃烧罐（23），多个传感器（22），多个传感器（22）中的每一个联接到相应的燃烧罐（23）和燃烧罐（23）的数量（23）以及控制器（24）。控制器（24）包括存储一个或多个处理器可执行例程的存储器（26,27）和被配置为访问并执行由存储器（26,27）编码的一个或多个例程的处理器（28,29）。该一个或多个例程在被执行时使得处理器（28,29）从多个传感器（22）接收一个或多个信号，将一个或多个信号转换为音频输出（34），并将转换后的音频输出（34）经由一个或多个音频输出设备（30,31）。

2. 发明公开

EP3215716A1 METHOD FOR DETERMINING ANGULAR POSITIONS OF MULTIPLE COMPRESSOR GUIDE VANES 审中-公开
标题翻译：确定多压缩机导向槽角位置的方法
公开(公告)号：EP3215716A1
公开(公告)日：2017-09-13
申请号：EP14905304.3
申请日：2014-11-04
申请人： Siemens Aktiengesellschaft
发明人： LAU, Ow , REN, Chao , WALLSTAB, Thomas
IPC分类号： F01D17/16
CPC分类号： F01D21/003 , F01D9/041 , F05D2260/30 , F05D2270/80 , G01B11/14 , G01B17/00
摘要： A method is for determining the angular positions of multiple compressor guide vanes. The method includes measuring the positions of at least two points on the circumference of the actuating ring, via at least two linear position sensors fixed on the compressor casing, and pointing at the actuating ring vertically at a time when the actuating ring deviates from its original position where the ring center coincides with the casing center; calculating the ring center offset based on the measured positions of the at least two points and the radius of the actuating ring; measuring the angle of one of the multiple guide vanes at the same time when measuring the positions of the at least two points; and calculating the angles of the multiple guide vanes based on the ring center offset and the angle of the guide vane. An actuation apparatus for multiple compressor guide vanes is included.
摘要翻译：一种用于确定多个压缩机导叶（10）的角位置的方法，包括：（a）通过至少两个线性位置传感器测量致动环（30）的圆周上的至少两个点（P1，Q1）的位置（40）上并且当致动环（30）偏离其环中心与套管中心重合的原始位置时垂直指向致动环（30）的装置（70,80）; （b）基于所述至少两个点（P1，Q1）的测量位置和所述致动环（30）的半径（r）来计算所述环中心偏移量（a1，b1）; （c）当测量所述至少两个点（P1，Q1）的位置时，同时测量所述多个导向叶片中的一个导向叶片的角度（αx）; （d）基于环形中心偏移量（a1，b1）和导向叶片的角度（αx）计算多个导向叶片（αi）的角度。还公开了用于多个压缩机导叶（10）的致动装置。

3. 发明公开

EP3153660A1 HEATING SYSTEMS FOR INTERNALLY HEATING ROTOR IN-SITU IN TURBOMACHINES, AND RELATED ROTOR 审中-公开
标题翻译：新泽西州涡旋发动机在ZUGEHÖRIGER转子的新型旋转器
公开(公告)号：EP3153660A1
公开(公告)日：2017-04-12
申请号：EP16192212.5
申请日：2016-10-04
申请人： General Electric Company
发明人： SYKES, Carey Lorne , FRUTSCHY, Kristopher John , KUDLACIK, Edward Leo , SYKES, Carey Lorne
IPC分类号： F01D5/08 , F01D11/24 , F01D25/10
CPC分类号： F01K3/186 , F01D5/08 , F01D11/24 , F01D25/10 , F05D2270/303 , F05D2270/80 , F05D2270/804
摘要： Heating systems (200) for a rotor (114, 210) in-situ in a turbomachine (90, 190) are provided. In contrast to conventional systems that merely heat from an external turbine (212) casing, embodiments of the disclosure heat the rotor (114, 210). In one embodiment, a heating system (200) includes a heating element (330, 430, 530) to heat a portion of an exterior surface (240) of the rotor (114, 210). In another embodiment, the heating system (200) may include a heating element(s) (330, 430, 530) at least partially positioned within the rotor (114, 210), and the rotor (114, 210) including the heating system (200). Each embodiment may include a controller (340) to control operation of the heating element(s) (330, 430, 530).
摘要翻译：提供了用于在涡轮机（90,190）中原位置的转子（114,210）的加热系统（200）。与仅仅从外部涡轮（212）壳体加热的常规系统相反，本公开的实施例加热转子（114,210）。在一个实施例中，加热系统（200）包括加热元件（330,430,530），以加热转子（114,210）的外表面（240）的一部分。在另一个实施例中，加热系统（200）可以包括至少部分地定位在转子（114,210）内的加热元件（330,430,530），并且转子（114,210）包括加热系统（200）。每个实施例可以包括用于控制加热元件（330,430,530）的操作的控制器（340）。

4. 发明公开

EP3071798A1 TURBOMACHINE ET PROCEDE DE REGULATION 有权转让
标题翻译： TURBINENMOTOR UND STEUERUNGSVERFAHREN
公开(公告)号：EP3071798A1
公开(公告)日：2016-09-28
申请号：EP14806031.2
申请日：2014-11-07
申请人： Turbomeca
发明人： LANGFORD, Stephen , LESCHER, Fabien
IPC分类号： F01D21/02 , F02C3/10 , F02C9/46
CPC分类号： F01D21/02 , F02C3/10 , F02C9/46 , F05D2220/329 , F05D2270/021 , F05D2270/09 , F05D2270/091 , F05D2270/80 , Y02T50/671
摘要： The invention relates to a method for controlling a turbine engine (5) which includes a compressor (8), a combustion chamber (9), first and second turbines (10, 12), a first rotary shaft (11) rotatably secured to said compressor and to said first turbine, a second rotary shaft (13) to which the second turbine is rotatably secured, said second rotary shaft being freely rotatable relative to the first rotary shaft, and a controller (15) for controlling the fuel supply to the combustion chamber. Said controller interrupts the fuel supply to the combustion chamber if a speed of rotation (N2) of said second rotary shaft exceeds a maximum threshold (N2imax) which varies according to at least one indicative physical parameter associated with a mechanical power extracted from combustion gases in the second turbine.
摘要翻译：涡轮发动机包括压缩机，燃烧室，燃烧室下游的第一和第二涡轮机，被限制为至少与压缩机和第一涡轮机一起旋转的第一旋转轴，被限制为与第二涡轮机一起旋转的第二旋转轴，第二旋转轴可相对于第一旋转轴自由旋转，以及用于控制向燃烧室供给燃料的调节器。如果第二旋转轴的旋转速度超过最大阈值，则调节器将燃料供给切断，该最大阈值随着至少一个指示物理参数的变化而变化，该物理参数与从燃烧气体中提取的机械功率相关联第二台涡轮。还提出了一种调节涡轮发动机的方法。

5. 发明公开

EP3014076A1 SYSTEMS AND METHODS FOR MONITORING GAS TURBINE SYSTEMS HAVING EXHAUST GAS RECIRCULATION 审中-公开
标题翻译：系统和方法燃气涡轮系统的带有废气再循环监测
公开(公告)号：EP3014076A1
公开(公告)日：2016-05-04
申请号：EP14742048.3
申请日：2014-06-24
申请人： ExxonMobil Upstream Research Company
发明人： MINTO, Karl Dean , BEADIE, Douglas Frank
IPC分类号： F01D17/02 , F02C3/34 , F02C9/28
CPC分类号： F02C3/34 , F01D17/02 , F02C3/20 , F02C9/00 , F02C9/28 , F05D2260/80 , F05D2270/0831 , F05D2270/80 , Y02E20/16 , Y02T50/677
摘要： A system includes a plurality of extraction passages configured to passively extract a portion of a gas flow from a downstream region of a gas flow path. The system includes a plurality of sensors respectively coupled to the plurality of extraction passages, wherein the plurality of sensors is configured to measure one or more parameters of the portion of the gas flow traversing the plurality of extraction passages. The system also includes a manifold coupled to the plurality of extraction passages, wherein the manifold is configured to receive the portion of the gas flow from the plurality of extraction passages. The system further includes a return passage coupled to the manifold, wherein the return passage is configured to passively provide the portion of the gas flow to an upstream region of the gas flow path.

6. 发明授权

EP2599968B1 Method of positioning a control surface to reduce hysteresis 失效转让
标题翻译：一种用于定位的控制表面，用于滞后的还原方法
公开(公告)号：EP2599968B1
公开(公告)日：2016-04-06
申请号：EP12190935.2
申请日：2012-11-01
申请人： Rolls-Royce plc
发明人： Moore, Jonathan , Haydn-Smith, Simon
IPC分类号： F01D17/16 , F02C9/20 , G05B15/02 , F04D27/00
CPC分类号： G05B15/02 , F01D17/085 , F01D17/162 , F01D17/24 , F02C9/20 , F04D27/001 , F05D2270/80 , G05B2219/41208

7. 发明公开

EP2412952A3 Aircraft engine control during icing of temperature probe 有权
标题翻译：冷冻温度探针在航空器的发动机控制
公开(公告)号：EP2412952A3
公开(公告)日：2015-02-18
申请号：EP11176212.6
申请日：2011-08-01
申请人： Pratt & Whitney Canada Corp.
发明人： Calandra, Salvatore , Giroux, Frederic , Iacobacci, Mark , Chabot, Martin , Hartropp, Simon , Syed, Yusuf , Chmiel, Dariusz , Balaj, Adrienne
IPC分类号： F02C7/047 , F01D25/02 , F02C9/28 , B64D15/12 , B64D15/20 , G01K13/02
CPC分类号： B64D31/06 , F01D25/02 , F02C7/047 , F02C9/28 , F02D9/00 , F05B2260/80 , F05B2270/303 , F05D2270/094 , F05D2270/303 , F05D2270/80 , G01K1/20 , G01K13/02 , G01K13/022 , G01K2013/024 , G01K2205/02 , G07C3/00
摘要： Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using (46) one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining (44) that an icing condition associated with the probe exists; and using (48) data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

8. 发明公开

EP2738372A1 Gas turbine temperature measurement 有权
标题翻译： Gasturbinen-Temperaturmessung
公开(公告)号：EP2738372A1
公开(公告)日：2014-06-04
申请号：EP13192826.9
申请日：2013-11-14
申请人： Alstom Technology Ltd
发明人： Lang, Wolfgang , Hoffmann, Juergen
IPC分类号： F02C9/28 , G01K11/24
CPC分类号： F02C9/28 , F02C6/003 , F05D2270/303 , F05D2270/80 , G01K11/24 , G01K13/02 , G01K2013/024 , G01M15/14 , Y02E20/14
摘要： Method for determining a temperature in a pressurized flow path of a gas turbine (10) comprising the steps of sending an acoustic signal from an acoustic signal emitting transducer (20, 21) across a section of the pressurized flow path, detecting the acoustic signal with a receiving transducer (20, 21), measuring the time needed by the acoustic signal to travel from the acoustic signal emitting transducer (20, 21) to the receiving transducer (20, 21), calculating the speed of sound, and calculating the temperature as a function of the speed of sound, the heat capacity ratio (κ) and a specific gas constant (R spec ) of the gas flowing in the pressurized flow path.
Gas turbine with a processor and transducers arranged to carry out such a method is disclosed.
摘要翻译：一种用于确定燃气轮机（10）的加压流路中的温度的方法，包括以下步骤：从声信号发射换能器（20,21）发出声信号，穿过加压流路的一部分，用接收换能器（20,21），测量声信号从声信号发射换能器（20,21）行进到接收换能器（20,21）所需的时间，计算声速并计算温度作为声速的函数，在加压流路中流动的气体的热容量比（º）和特定气体常数（R spec）。公开了具有处理器和布置成执行这种方法的换能器的燃气轮机。

9. 发明公开

EP2599968A1 Method of positioning a control surface to reduce hysteresis 失效转让
标题翻译：一种用于定位的控制表面，用于滞后的还原方法
公开(公告)号：EP2599968A1
公开(公告)日：2013-06-05
申请号：EP12190935.2
申请日：2012-11-01
申请人： Rolls-Royce plc
发明人： Moore, Jonathan , Haydn-Smith, Simon
IPC分类号： F01D17/16 , F02C9/20 , G05B15/02 , F04D27/00
CPC分类号： G05B15/02 , F01D17/085 , F01D17/162 , F01D17/24 , F02C9/20 , F04D27/001 , F05D2270/80 , G05B2219/41208
摘要： A method of determining the actual position of a control surface (27). The method comprises receiving a signal (34) representative of a required position of the control surface (27), repositioning the control surface (27) in response to the signal (34) by moving an actuator (26), measuring a secondary position indicator, calculating the actual position of the control surface (27) on the basis of the secondary position indicator and, comparing the actual position with the required position.
摘要翻译：确定性采矿的方法的控制表面（27）的实际位置。该方法包括接收一个信号（34）代表的控制表面（27）的所需位置的，通过移动到致动器（26）响应于所述信号（34）重新定位所述控制表面（27），测量二次位置指示器，计算二次位置指示器的基础上控制表面（27）的实际位置，并且比较所需要的位置的实际位置。

10. 发明公开

EP2505985A2 Combustor probe for gas turbine 审中-公开
标题翻译： BrennkammersondefürGasturbinen
公开(公告)号：EP2505985A2
公开(公告)日：2012-10-03
申请号：EP12161606.4
申请日：2012-03-27
申请人： General Electric Company
发明人： Romig, Bryan Wesley , Kegley, Jonathan Hale , Clifford, Robert Wade , Simons, Derrick Walter
IPC分类号： G01N1/22
CPC分类号： G01N1/2252 , F01D21/003 , F05D2270/80 , F23N5/003 , F23N5/18 , F23N2031/18 , F23N2041/20 , F23N2900/05005 , F23R3/00
摘要： Embodiments of the present disclosure are directed towards a turbine combustor probe (84) having a combustion dynamics monitoring probe (102) configured to monitor combustion dynamics within a turbine combustor (14). The turbine combustor probe (84) also has a gas sampling sleeve (100) configured to collect a gas sample from an airflow path (56) between a liner (58) and a flow sleeve (60) of the turbine combustor (14).
摘要翻译：本公开的实施例涉及具有燃烧动力学监测探头（102）的涡轮机燃烧器探头（84），其被配置为监测涡轮机燃烧器（14）内的燃烧动力学。涡轮机燃烧器探头（84）还具有气体采样套管（100），其构造成从涡轮机燃烧器（14）的衬套（58）和流动套筒（60）之间的气流通道（56）收集气体样品。

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