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1. 发明授权

EP2694878B1 GASTURBOGRUPPE UND ZUGEHÖRIGES BETRIEBSVERFAHREN 有权
公开(公告)号：EP2694878B1
公开(公告)日：2018-12-12
申请号：EP12717070.2
申请日：2012-04-05
申请人： Ansaldo Energia Switzerland AG
发明人： MARMILIC, Robert , HELLAT, Jaan , FREITAG, Ewald , EROGLU, Adnan
IPC分类号： F23C6/04 , F02C7/141 , F02C7/228
CPC分类号： F02C3/00 , F02C7/141 , F02C7/228 , F05D2220/722 , F23R3/346 , F23R2900/03341 , Y02E20/16 , Y02E20/18 , Y02T50/671 , Y02T50/675

2. 发明授权

EP2535644B1 Combustor fuel control systems with flow divider assemblies 失效转让
公开(公告)号：EP2535644B1
公开(公告)日：2018-10-24
申请号：EP12169406.1
申请日：2012-05-24
申请人： Honeywell International Inc.
发明人： Zielinski, Edward
IPC分类号： F23K5/06 , F23K5/14 , F23N1/00 , F02C7/228
CPC分类号： F23K5/06 , F02C7/228 , F23K5/14 , F23K5/147 , F23K2900/05001 , F23K2900/05141 , F23N1/00 , Y10T137/0318 , Y10T137/0363 , Y10T137/2521 , Y10T137/2524 , Y10T137/2559
摘要： A flow divider assembly (130) includes a dividing valve (220) and a balancing valve (270). The dividing valve includes a dividing cavity (222) configured to receive a flow of fuel and a piston device (250) arranged within the dividing cavity and selectively positioned to divide the flow of fuel in the dividing cavity into the first dividing valve port (234) and the second dividing valve port (236). The balancing valve (270) is fluidly coupled to the dividing valve (220) and configured to receive the first portion and the second portion of the flow. The balancing valve (270) includes a balancing cavity (272) and a balancing device (290) arranged within the balancing cavity and selectively positioned to direct the first portion of the flow into the first balancing cavity port (286) at a third pressure and the second portion of the flow into the second balancing cavity port (288) at a fourth pressure such that the first pressure is approximately equal to the second pressure.

3. 发明授权

EP3217000B1 COMBUSTION STAGING SYSTEM 有权
公开(公告)号：EP3217000B1
公开(公告)日：2018-09-26
申请号：EP17154954.6
申请日：2017-02-07
申请人： Rolls-Royce PLC
发明人： HILL, Ralph, W.
IPC分类号： F23R3/34 , F02C9/46 , F02C9/26 , F02C7/14 , F01D21/00 , F02C7/232 , F02C7/228 , F02C7/22
CPC分类号： F02C9/46 , F01D21/003 , F02C7/14 , F02C7/222 , F02C7/228 , F02C7/232 , F02C9/263 , F05D2220/32 , F05D2240/35 , F05D2260/80 , F23R3/343 , F23R3/346
摘要： A combustion staging system for fuel burners of a multi-stage combustor of a gas turbine engine is provided. The system has pilot and mains fuel manifolds respectively distributing fuel to pilot and mains stages of the burners. The system further has a plurality of check valves through which the mains manifold feeds fuel to the respective burners. The check valves are arranged to open when the fuel pressure within the mains manifold exceeds a predetermined fuel pressure relative to gas pressure in the combustor. The system further has a splitting unit which receives a metered fuel flow and controllably splits the received fuel flow into pilot and mains flows which are sent respectively to the pilot and mains fuel manifolds to perform staging control of the combustor. The splitting unit is operable to select the pilot manifold and to deselect the mains manifold for pilot-only operation in which there is a pilot supply to the combustor but no mains supply to the combustor from the burners. It is also operable to select both the pilot and mains manifolds for pilot and mains operation in which there are pilot and mains supplies to the combustor from the burners. The system further has a cooling flow recirculation line having a delivery section arranged to provide a cooling flow of fuel to the mains manifold when that manifold is deselected so that the deselected mains manifold remains primed with relatively cool fuel, and a return section arranged to collect the cooling flow from the mains manifold. The system further has a gas pressure sensor configured to measure gas pressure in the combustor, a speed sensor which measures a rotation speed of a rotor of the engine, and a control unit which, when the mains manifold is deselected for pilot-only operation, (i) compares the measured rotation speed with a predicted rotation speed for the metered fuel flow, and compares the measured gas pressure with a predicted gas pressure for the metered fuel flow, and (ii) is adapted to close off the recirculation line when the results of these comparisons are indicative of leakage of fuel from the cooling fuel flow into the combustor through one or more of the check valves.

4. 发明授权

EP3071886B1 DISPOSITIF D'INJECTION MULTIPOINT ET PROCÉDÉ D'INJECTION POUR MOTEUR D'AÉRONEF 有权
公开(公告)号：EP3071886B1
公开(公告)日：2018-09-05
申请号：EP14821722.7
申请日：2014-11-20
申请人： Safran Aircraft Engines
发明人： CHALAUD, Sébastien
IPC分类号： F23R3/34 , F23D11/00 , F23K5/06 , F02C9/34 , F02C7/228 , F02C7/232 , F02M41/04
CPC分类号： F23R3/34 , F02C7/228 , F02C7/232 , F02C9/34 , F23D11/00 , F23D2209/30 , F23K5/06 , F23K2203/105 , F23K2301/203

5. 发明授权

EP2568218B1 Fuel gas pressure control system and method for reducing gas turbine fuel supply pressure requirements 有权
公开(公告)号：EP2568218B1
公开(公告)日：2018-08-08
申请号：EP12183151.5
申请日：2012-09-05
申请人： GENERAL ELECTRIC COMPANY
发明人： Rentala, Pradeep
IPC分类号： F23K5/00 , F23N1/00 , F23R3/28 , F02C7/228 , F02C9/26 , F02C9/34 , F23N5/18
CPC分类号： F23N1/002 , F02C7/228 , F02C9/263 , F05D2270/301 , F23K5/005 , F23N2005/185 , F23R3/28
摘要： A method is provided for modifying a fuel control system for a gas turbine (10) having a standard unloading sequence and a pre-defmed minimum inlet pressure requirement associated with the standard unloading sequence to allow the gas turbine to operate over an increased range of fuel supply pressure. The method includes modifying the fuel control system by inputting a modified unloading sequence onto a computing system (28) operatively associated with the fuel control system (24,30), the modified unloading sequence comprising a series of operating modes, mode transfers, or a combination thereof that is different than the standard unloading sequence; and modifying the fuel control system by inputting a new defined minimum inlet pressure requirement for the modified unloading sequence onto the computing system, the new defined minimum inlet pressure requirement being less than the pre-defined minimum inlet pressure requirement thereby reducing a fuel supply pressure trip point for the gas turbine.

6. 发明授权

EP2511499B1 Fuel flow divider and ecology system for a gas turbine engine fuel flow control system 失效转让
公开(公告)号：EP2511499B1
公开(公告)日：2018-07-11
申请号：EP12162915.8
申请日：2012-04-02
申请人： Honeywell International Inc.
发明人： Futa, Paul , McRoberts, Brad , Lafferty, Greg
IPC分类号： F02C7/232 , F02C9/26 , F02C7/228 , F02C9/34
CPC分类号： F02C9/263 , F02C7/228 , F02C7/232 , F02C9/34 , Y10T137/2524
摘要： A flow divider valve for a gas turbine engine fuel supply system is provided. The flow divider valve is configured, whenever fuel pressure at its inlet port is between a first predetermined pressure and a second predetermined pressure, to supply the fuel to a start nozzle manifold outlet port at a substantially constant flow rate, and to direct any fuel flow in excess of the substantially constant flow rate to a run nozzle manifold outlet port.

7. 发明公开

EP3301361A1 PILOT/MAIN FUEL SHIFTING IN AN AXIAL STAGE COMBUSTOR FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气涡轮发动机轴流式燃烧室中的试验/主燃料切换
公开(公告)号：EP3301361A1
公开(公告)日：2018-04-04
申请号：EP17193551.3
申请日：2017-09-27
申请人： United Technologies Corporation
发明人： PROSCIA, William
IPC分类号： F23N1/00 , F23N5/00 , F23N5/16 , F23R3/34
CPC分类号： F02C7/228 , F05D2220/323 , F05D2240/35 , F05D2270/31 , F05D2270/333 , F05D2270/335 , F23N1/002 , F23N5/003 , F23N5/16 , F23R3/002 , F23R3/343 , F23R3/346 , Y02T50/677
摘要： A combustor (56) of a gas turbine engine (20) includes an axial fuel injection system (92) in communication with a combustion chamber (56), the axial fuel injection system (92) operable to supply a first percentage of fuel and a radial fuel injection system (120) that communicates with the combustion chamber (56) downstream of the axial fuel injection system (92), the radial fuel injection system (120) operable to supply a second percentage of fuel, the first percentage and the second percentage of fuel scheduled in response to an engine operating parameter.
摘要翻译：燃气涡轮发动机（20）的燃烧器（56）包括与燃烧室（56）连通的轴向燃料喷射系统（92），所述轴向燃料喷射系统（92）可操作以供应第一百分比的燃料和在所述轴向燃料喷射系统（92）下游与所述燃烧室（56）连通的径向燃料喷射系统（120），所述径向燃料喷射系统（120）可操作以提供第二百分比的燃料，所述第一百分比和所述第二根据发动机运行参数计划的燃料的百分比。

8. 发明授权

EP1555484B1 Verfahren zum Betreiben einer Gasturbinen-Brennkammer 有权
标题翻译：用于运行燃气轮机燃烧器的方法
公开(公告)号：EP1555484B1
公开(公告)日：2018-03-21
申请号：EP05100186.5
申请日：2005-01-13
申请人： Ansaldo Energia IP UK Limited
发明人： Cerny, Jan, Dr. , Jhalani, Anurag
IPC分类号： F23N1/02 , F23R3/36 , F23R3/34 , F23D17/00 , F23D23/00 , F02C7/228
CPC分类号： F23D23/00 , F02C7/228 , F23C2900/07002 , F23D17/002 , F23N1/022 , F23N2037/02 , F23R3/34

9. 发明授权

EP2204563B1 Operating a turbine at baseload on cold fuel with hot fuel combustion hardware 有权
标题翻译：使用热燃料燃烧硬件在基本冷负荷下运行涡轮机
公开(公告)号：EP2204563B1
公开(公告)日：2018-02-21
申请号：EP09179164.0
申请日：2009-12-15
申请人： General Electric Company
发明人： Fuller, Jason D , Frederick, Garth C , Maters, John C , Morgan, Douglas C , Flamand, Luis M
IPC分类号： F02C7/228 , F02C9/34 , F02C9/40 , F23R3/34 , F23R3/36
CPC分类号： F02C7/228 , F02C9/34 , F02C9/40 , F05D2270/08 , F05D2270/09 , F05D2270/31 , F23N2021/10 , F23N2041/20 , F23R3/34 , F23R3/36 , F23R2900/00013
摘要： A method and algorithm are provided to operate a gas turbine at baseload in an emission compliant capable mode to avoid combustion dynamics while operating with cold fuel and hot fuel combustion hardware. A designated fuel split for avoiding combustion dynamics is scheduled (155) when a temperature for a gas fuel is below a designated value. Interlocks preventing mode transitions with cold fuel are disabled (130, 135). A determination (160) is made whether a modified wobbe index for the gas fuel is below an emissions compliant value. An alarm is activated (165) if the modified wobbe index is below the emissions compliant value to notify the operator of a potential emissions shift.

10. 发明公开

EP3260781A1 MULTI-TUBE LATE LEAN INJECTOR 有权
标题翻译：多管尾部精益注射器
公开(公告)号：EP3260781A1
公开(公告)日：2017-12-27
申请号：EP17176843.5
申请日：2017-06-20
申请人： General Electric Company
发明人： BERRY, Jonathan Dwight , HUGHES, Michael John
IPC分类号： F23R3/34 , F23R3/06 , F23R3/28
CPC分类号： F23R3/286 , F02C7/222 , F02C7/228 , F23R3/06 , F23R3/346 , F23R2900/03341
摘要： A micromixer injector (200) includes a fuel plenum (230) to receive a supply of fuel. A plurality of premixing tubes (220) extend through the fuel plenum. Each tube has a plurality of fuel holes (225) formed therein to receive the supply of fuel for mixing with air in the tube. The micromixer has a tapering profile such that an overall inlet area (232) of the plurality of premixing tubes on an upstream face of the micromixer is larger than an overall outlet area (236) of the plurality of premixing tubes on a downstream face such that the plurality of premixing tubes are relatively spaced-apart at the upstream face and more densely packed at the downstream face. Additionally, an air inlet (223) of each tube has a first geometrical shape and the outlet (227) of each tube has a second geometrical shape that is different from the first geometrical shape.
摘要翻译：微混合器喷射器（200）包括用于接收燃料供应的燃料增压室（230）。多个预混合管（220）延伸穿过燃料室。每个管具有形成在其中的多个燃料孔（225），以接收与管中的空气混合的燃料供应。微混合器具有逐渐变细的轮廓，使得微混合器的上游面上的多个预混合管的总体入口面积（232）大于下游面上的多个预混合管的总体出口面积（236），使得多个预混合管在上游面处相对间隔开并且在下游面处更密集地堆积。另外，每个管的空气入口（223）具有第一几何形状，并且每个管的出口（227）具有与第一几何形状不同的第二几何形状。

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