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公开(公告)号：EP3410092A1
公开(公告)日：2018-12-05
申请号：EP18171482.5
申请日：2018-05-09
发明人： SUNDARARAJAN, GURUPRASAD NMN , PILLAI, Prashanth , Krishnan R., Murali , HEFNER, Rebecca , FOULKES, Bradford , VISWANATHAN, Anbarasan , KELLY, Robert G.
IPC分类号： G01M15/14
CPC分类号： F04D27/001 , F05D2220/32 , F05D2230/80 , F05D2240/20 , F05D2260/80 , F05D2260/81 , F05D2260/821 , F05D2270/306 , F05D2270/311 , F05D2270/313 , G01M15/14 , G01N17/04 , G05B13/048
摘要： A control system (100) and method utilizing one or more processors (110) that are configured to determine contaminant loading of blades (106) of a turbomachinery compressor (102) based on one or more environmental conditions to which the turbomachinery compressor (102) is exposed and one or more atmospheric air inlet conditions of the turbomachinery compressor (102). The one or more processors (110) then determine a corrosion contaminant concentration on the blades (106) of the turbomachinery compressor (102) based on the contaminant loading that is determined and determine an upper limit on or a distribution of potential corrosion of the blades (106) of the turbomachinery (102) based on the corrosion contaminant concentration, at least one of the environmental conditions to which the turbomachinery compressor (102) is exposed, and the corrosion contaminant concentration that is determined.
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公开(公告)号：EP3324021A1
公开(公告)日：2018-05-23
申请号：EP16382541.7
申请日：2016-11-21
发明人： CHIABRANDO, Marcos, Javier , CARRO SANCHEZ, Miguel Angel , MARTINEZ SANCHO, Alberto , MARTINEZ VILLACORTA, Samuel , FERNANDEZ-LOPEZ, Pio
IPC分类号： F02C7/277
CPC分类号： F02C7/27 , F02C7/12 , F02C7/277 , F05D2220/323 , F05D2220/50 , F05D2270/02 , F05D2270/301 , F05D2270/3013 , F05D2270/313
摘要： The present invention refers to a system for controlling aircraft main engines cooling during starting operations. An aircraft incorporates a main engine and a pneumatic starter for starting the same, and a pneumatic source fluidly communicated with the pneumatic starter to supply pressurized air thereto. According to the invention, a control system is provided with a data chart containing predetermined pressure values of the pneumatic source, and said values corresponds to an ambient condition to obtain a desired rotating speed for the main engine for that ambient condition. The control system is adapted for controlling the pneumatic source air pressure output based on said data chart, to rotate the main engine within a predefined rotating speed range during cooling procedure. The invention provides a controlled reduced rotating speed during main engines cooling or cranking operation before starting main engines, in order to mitigate bowed rotor phenomenon.
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公开(公告)号：EP2604826A3
公开(公告)日：2017-05-17
申请号：EP12196597.4
申请日：2012-12-11
CPC分类号： F01K13/00 , F01D19/00 , F01D19/02 , F01D25/10 , F01K13/02 , F01K23/101 , F02C6/18 , F02C9/00 , F02C9/28 , F05D2220/72 , F05D2260/20 , F05D2270/301 , F05D2270/303 , F05D2270/3061 , F05D2270/311 , F05D2270/313 , F05D2270/332 , F05D2270/335 , Y02E20/16
摘要： A system for warming up a steam turbine (38) includes a gas turbine (12) and a controller (50) operably connected to the gas turbine (12). The controller (50) is programmed to receive a plurality of measured input signals (52) and control the gas turbine (12) to produce an exhaust having a desired energy. A first measured input signal (54,56,58,60) is reflective of a measured operating parameter of the gas turbine (12) and a second measured input signal (62,64) is reflective of an operating parameter of the steam turbine. A method for warming up a steam turbine (38) includes sending a plurality of measured input signals (52) to a controller (50), wherein a first measured input signal (52) reflects a measured operating parameter of a gas turbine and a second measured input signal (62,64) reflects an operating parameter of the steam turbine. The method further includes controlling the gas turbine based on the plurality of measured input signals (52) and producing an exhaust from the gas turbine (12), wherein the exhaust has a desired energy.
摘要翻译： 用于预热蒸汽轮机（38）的系统包括燃气轮机（12）和可操作地连接到燃气轮机（12）的控制器（50）。 控制器（50）被编程为接收多个测量的输入信号（52）并且控制燃气轮机（12）产生具有期望能量的排气。 第一测量输入信号（54,56,58,60）反映燃气轮机（12）的测量操作参数，第二测量输入信号（62,64）反映蒸汽轮机的操作参数。 一种用于预热蒸汽涡轮机（38）的方法包括将多个测量的输入信号（52）发送到控制器（50），其中第一测量的输入信号（52）反映燃气涡轮机的测量的运行参数，并且第二 测量的输入信号（62,64）反映蒸汽轮机的运行参数。 该方法进一步包括基于多个测量的输入信号（52）来控制燃气轮机并且从燃气轮机（12）产生排气，其中排气具有期望的能量。
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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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公开(公告)号：EP2808493B1
公开(公告)日：2016-03-16
申请号：EP14170149.0
申请日：2014-05-28
发明人： Nanataki, Kenji , Kuroki, Hidetoshi
CPC分类号： F01D15/10 , F02C3/10 , F02C9/18 , F05D2270/05 , F05D2270/313
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公开(公告)号：EP2789537B1
公开(公告)日：2016-01-20
申请号：EP14161859.5
申请日：2014-03-26
发明人： Shepard, Eric , Wolownik, Todd
CPC分类号： B64D41/00 , B64D13/06 , B64D2013/0611 , B64D2013/0618 , B64D2013/0648 , F02C6/08 , F02C7/141 , F02C7/32 , F02C9/18 , F05D2270/313 , Y02T50/56
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公开(公告)号：EP2447509A2
公开(公告)日：2012-05-02
申请号：EP11174978.4
申请日：2011-07-22
申请人： Hitachi Ltd.
发明人： Saito, Nozomi , Saito, Takeo , Nanataki, Kenji
CPC分类号： F02C9/28 , F02C3/10 , F02C9/20 , F02C9/263 , F02C9/34 , F02C9/54 , F05D2220/76 , F05D2240/35 , F05D2260/99 , F05D2270/304 , F05D2270/313
摘要： Provided are a combustor control method and a combustor controller capable of calculating the combustion air flow and the fuel flow in multi-shafts gas turbine with high precision and without the need of performing complicated calculations and thereby calculating a fuel-air ratio necessary for stable combustion control. The multi-shaft gas turbine is made up of a gas generator turbine 110 and a power turbine 120. A combustor 114 includes a diffusive combustion unit F1 and a plurality of premixed combustion units F21 - F24. An ignition/extinction control unit 220 of the combustor control device calculates the combustion air flow supplied to the combustor 114 based on the open position of compressor inlet guide vanes 112A attached to the gas generator turbine 110, revolution speed of the gas generator turbine 110 and compressor inlet temperature, calculates the flow of fuel supplied to the combustor 114 based on revolution speed of the power turbine 120, and calculates the fuel-air ratio in real time as flame reference based on the calculated combustion air flow and fuel flow.
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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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公开(公告)号：EP3102809A4
公开(公告)日：2017-11-08
申请号：EP14880997
申请日：2014-10-03
CPC分类号： B64D37/34 , B64D27/10 , F02C7/06 , F02C7/14 , F02C7/22 , F02C7/224 , F02C9/28 , F05D2220/323 , F05D2260/213 , F05D2270/20 , F05D2270/313 , Y02T50/675
摘要： A method of protecting fuel hardware for a gas turbine engine in an aircraft is disclosed. The method may include determining a current altitude of the aircraft, and controlling a temperature of fuel for the gas turbine engine based at least in part on the current altitude. A thermal management system for a gas turbine engine in an aircraft is also disclosed. The thermal management system may include a sensor configured to detect a current altitude of the aircraft, and a controller in operative communication with the sensor. The controller may be configured to manage a fuel temperature for the gas turbine engine based at least in part on the current altitude detected by the sensor.
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10.发明公开Method and Apparatus for Optimizing the Operation of a Turbine System Under Flexible Loads 审中-公开用于优化涡轮机系统的具有灵活负荷操作的方法和装置
公开(公告)号：EP2597288A3
公开(公告)日：2017-06-14
申请号：EP12193660.3
申请日：2012-11-21
发明人： Freeman, Thomas John , Obenhoff, Ryan Eric , Klosinski, Joseph , Cocca, Michael Anthony , Scipio, Alston I. , Yarnold, Mike , Ekanayake, Sanji , Warwick, Douglas Corbin
CPC分类号： F02C9/18 , F01K23/10 , F02C3/13 , F02C3/34 , F02C7/057 , F02C9/22 , F02C9/26 , F02C9/28 , F02C9/48 , F05D2220/722 , F05D2260/601 , F05D2270/08 , F05D2270/3061 , F05D2270/313 , F23R3/26 , Y02E20/14 , Y02E20/16 , Y02E20/18
摘要： A gas turbine system (1) includes a compressor protection subsystem (5); a hibernation mode subsystem (7); and a control subsystem (1) that controls the compressor subsystem (5) and the hibernation subsystem (7). At partial loads on the turbine system (1), the compressor protection subsystem (5) maintains an air flow through a compressor (13) at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor (13). The air fuel ratio in a combustor (15) is maintained where exhaust gas emission components from the turbine (17)are maintained below a predetermined component emission level while operating at partial loads.
摘要翻译： 一种燃气涡轮机系统（1）包括压缩机保护子系统（5）; 休眠模式子系统（7）; 和一个控制子系统（1）控制所述压缩机确实子系统（5）和冬眠子系统（7）。 在涡轮机系统（1）上部分负荷，该压缩机保护子系统（5）通过在压缩机（13）的空气流的保持在气流系数高于最小流率系数的部分负载，其中航空机械应力在压缩机发生时（ 13）。 在燃烧器（15）的空气燃料比维持在从涡轮机（17）的排气排放组分保持低于预定部件发射电平，而在部分负载运行。
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