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81. 发明申请

US20040146826A1 Venturi cluster, and burners and methods employing such cluster 审中-公开
标题翻译：文丘里集群，以及采用这种集群的燃烧器和方法
公开(公告)号：US20040146826A1
公开(公告)日：2004-07-29
申请号：US10759323
申请日：2004-01-16
申请人： John Zink Company, LLC
发明人： Roger L. Poe , Wesley Ryan Bussman , I-Ping Chung , Ralph Robert Hayes , Jaiwant D. Jayakaran , Andrew Jones , Jason D. McAdams , Demetris T. Venizelos , Richard T. Waibel
IPC分类号： F23Q009/00 , F23D014/62
CPC分类号： F23L7/00 , F23C6/047 , F23C9/00 , F23C2202/20 , F23D14/04 , F23D14/08 , F23D14/10 , F23D14/64 , F23D2900/00015 , F23D2900/14063 , F23D2900/14642 , F23L2900/07002 , Y10T137/87281 , Y10T137/87571
摘要： A burner arrangement includes a venturi cluster including a plurality of venturis arranged for parallel flow. The multi venturi arrangement utilizing pressurized fuel as the inducing fluid to induce a flow of air enables the provision of an ultra fuel lean premix of fuel and air. A central burner tube which extends outwardly beyond the delivery end of a primary burner tip and mounts a relatively small capacity nozzle at a substantial distance from the delivery end of the burner tip enabling the ultra fuel lean mixture to expand and slow down such that its linear speed does not exceed the flame speed of the mixture prior to by the flame of the spaced nozzle. A deflector may be positioned adjacent the nozzle to assist in stabilizing the flame after the expansion and slowing process has been completed.

82. 发明授权

US06763664B2 Fuel ratio control method and device in a gas turbine combustor 失效
标题翻译：燃气轮机燃烧器中的燃料比控制方法和装置
公开(公告)号：US06763664B2
公开(公告)日：2004-07-20
申请号：US10262970
申请日：2002-10-03
申请人： Kuniaki Aoyama
发明人： Kuniaki Aoyama
IPC分类号： F02G900
CPC分类号： F02C7/228 , F01D17/02 , F05D2270/14 , F23D2900/00015 , F23N5/184 , F23N2041/20
摘要： A fuel ratio control method and a device therefor in a gas turbine combustor are provided in which supply ratio of pilot fuel to main fuel is appropriately maintained to thereby avoid unstable combustion, such as combustion vibration or misfire, and to realize a low NOx combustion. Fuel ratio control signal CSO is set corresponding to generator output LGEN put out by a generator output input unit 1. Pilot fuel ratio control is performed by correcting the fuel ratio control signal CSO corresponding to condition change in both or either one of combustion air and fuel. The condition change in the combustion air is at least one of changes in compressor on-line vane washing, ambient humidity, ambient pressure, etc. and the condition change in the fuel is a change in fuel component. The signal correction is also made by gas turbine deterioration factor or change rate in the generator output.
摘要翻译：提供了一种燃气轮机燃烧器中的燃料比控制方法及其装置，其中适当地维持引燃燃料与主燃料的供给比，从而避免不稳定的燃烧，例如燃烧振动或失火，并实现低NOx燃烧。燃料比控制信号CSO被设定为与由发电机输出单元1输出的发电机输出LGEN相对应。通过校正燃烧空气和燃料两者或任何一种中的条件变化对应的燃料比控制信号CSO来执行先导燃料比控制。燃烧空气中的状态变化是压缩机在线叶片洗涤，环境湿度，环境压力等的变化中的至少一种，并且燃料中的状态变化是燃料成分的变化。信号校正也由燃气轮机劣化因子或发电机输出的变化率进行。

83. 发明授权

US06736338B2 Methods and apparatus for decreasing combustor emissions 失效
标题翻译：减少燃烧器排放的方法和装置
公开(公告)号：US06736338B2
公开(公告)日：2004-05-18
申请号：US10361049
申请日：2003-02-07
申请人： Arthur Wesley Johnson , Robert Andrew Wade , David Louis Burrus
发明人： Arthur Wesley Johnson , Robert Andrew Wade , David Louis Burrus
IPC分类号： A62C208
CPC分类号： F23R3/343 , F23D2900/00015 , F23R3/16 , F23R3/283
摘要： A combustor for a gas turbine engine operates with high combustion efficiency, and low nitrous oxide emissions during engine operations. The combustor includes at least one trapped vortex cavity, a fuel delivery system including two fuel circuits, and a fuel spray bar assembly. A pilot fuel circuit supplies fuel to the trapped vortex cavity and a main fuel circuit supplies fuel to the combustor. The fuel spray bar assembly includes a spray bar and a heat shield. The spray bar is sized to fit within the heat shield. The heat shield includes aerodynamically-shaped upstream and downstream sides.
摘要翻译：用于燃气涡轮发动机的燃烧器以高燃烧效率运行，并且在发动机运行期间运行低一氧化二氮排放。燃烧器包括至少一个被捕获的涡流腔，包括两个燃料回路的燃料输送系统和燃料喷射杆组件。导向燃料回路将燃料供给到被捕获的涡流空腔，主燃料回路将燃料供给燃烧器。燃料喷射杆组件包括喷射杆和隔热罩。喷杆尺寸适合装在隔热罩内。隔热罩包括空气动力学形状的上游侧和下游侧。

84. 发明申请

US20040079086A1 Piloted airblast lean direct fuel injector with modified air splitter 有权
标题翻译：带改装空气分配器的先导式吹气机直喷式燃油喷射器
公开(公告)号：US20040079086A1
公开(公告)日：2004-04-29
申请号：US10278922
申请日：2002-10-24
申请人： Rolls-Royce, plc
发明人： Clifford E. Smith , Daniel A. Nickolaus
IPC分类号： F23R003/14
CPC分类号： F23R3/343 , F23D2900/00015 , F23D2900/00018 , F23R3/14 , F23R3/18
摘要： A fuel injector system that reduces and/or eliminates combustion instability. The fuel injector system includes a pilot fuel injector, a pilot swirler that swirls air past the pilot fuel injector, a main airblast fuel injector having an aft end, inner and outer main swirlers that swirl air past the main airblast fuel injector, and an air splitter located between the pilot swirler and the inner main swirler. The air splitter includes at least one aft end cone angled radially outboard and axially positioned downstream of the main airblast fuel injector aft end. The air splitter divides a pilot air stream exiting the pilot swirler from an inner main air stream exiting the inner main swirler to create a bifurcated recirculation zone.
摘要翻译：一种减少和/或消除燃烧不稳定性的燃料喷射器系统。燃料喷射器系统包括一个先导燃料喷射器，一个使空气旋转通过引燃燃料喷射器的先导旋流器，一个具有后端的主喷气燃料喷射器，旋转空气通过主喷气喷射器的内部和外部主旋流器，以及空气分配器位于飞行员旋流器和内部主旋流器之间。空分器包括至少一个后端锥体，其在径向外侧成角度并且轴向地位于主喷气喷射器后端的下游。空气分配器将离开先导旋流器的先导气流与离开内部主旋流器的内部主空气流分开，以产生分叉的再循环区。

85. 发明授权

US06632084B2 Burner configuration with primary and secondary pilot burners 有权
标题翻译：燃烧器配置与主要和次要驾驶燃烧器
公开(公告)号：US06632084B2
公开(公告)日：2003-10-14
申请号：US09794662
申请日：2001-02-27
申请人： Peter Berenbrink
发明人： Peter Berenbrink
IPC分类号： F23Q300
CPC分类号： F23D17/002 , F23D2206/10 , F23D2209/10 , F23D2209/20 , F23D2900/00014 , F23D2900/00015 , F23R3/343
摘要： A burner configuration with primary and secondary pilot burners is described. The burner configuration is used in a firing installation, in particular a gas turbine combustion chamber, and has a main burner and, disposed centrally within it, a primary pilot burner used for igniting and/or for stabilizing the combustion of the main burner. For additional stabilization, for reducing rumble noises in the firing installation and for avoiding the possible flashback of the flame in a partial region of the burner, which can then sometimes occur, a plurality of outlet openings, which together form a secondary pilot burner, are disposed in the outlet region of the main burner. The flames of the secondary pilot burner surround the main flame like a ring and additionally stabilize the operation under different load conditions.
摘要翻译：描述了具有主要和次要先导燃烧器的燃烧器配置。燃烧器配置用于燃烧装置，特别是燃气轮机燃烧室，并具有主燃烧器，并且设置在其内部，用于点燃和/或稳定主燃烧器燃烧的主引燃燃烧器。为了进一步的稳定化，为了减少点火装置中的隆隆声，并且为了避免在燃烧器的局部区域中可能发生的火焰的闪回，这可能会有时会发生，多个出口开口一起形成次级引燃燃烧器设置在主燃烧器的出口区域。次级引燃燃烧器的火焰围绕主火焰像环，并且另外在不同的负载条件下稳定操作。

86. 发明授权

US06532726B2 Gas-turbine engine combustion system 有权
标题翻译：燃气轮机发动机燃烧系统
公开(公告)号：US06532726B2
公开(公告)日：2003-03-18
申请号：US09240245
申请日：1999-01-29
申请人： Eric Roy Norster , Simon DePietro , Mahmoud Kowkabi , Hoger Gunter Heinrich Hesse
发明人： Eric Roy Norster , Simon DePietro , Mahmoud Kowkabi , Hoger Gunter Heinrich Hesse
IPC分类号： F02C900
CPC分类号： F23D14/24 , F23C7/002 , F23C2202/40 , F23D14/76 , F23D17/002 , F23D2206/10 , F23D2214/00 , F23D2900/00015 , F23R3/36
摘要： A gas-turbine engine combustion system has a combustor with a burner head having both pilot gas and pilot liquid-fuel injection arrangements, the pilot gas arrangement comprising an annular gallery communicating with a downstream face of the head and a deflecting arrangement adjacent the gallery for directing the pilot gas-fuel towards a longitudinal axis of the combustor and over a central part of the downstream face. The combustion system is designed so that, during both gas- and liquid-fuel operations, the flame front face is located close to the burner head and, during liquid-fuel operation, air is forced across the downstream face to cool the head. Advantageously, the cooling air is made to replace the pilot gas-fuel in the annular gallery, so that it is deflected, like the gas-fuel, and contacts the central part of the downstream face. The burner head also features main gas and liquid-fuel injection arrangements, these communicating with one or more passageways in a radial swirler attached to the head.
摘要翻译：燃气涡轮发动机燃烧系统具有燃烧器，燃烧器头具有先导气体和先导液体 - 燃料喷射装置，所述先导气体装置包括与头部的下游面连通的环形镜片和邻近画廊的偏转装置将先导气体燃料引导到燃烧器的纵向轴线并且在下游面的中心部分上。燃烧系统被设计成使得在气体和液体燃料操作期间，火焰前面靠近燃烧器头部，并且在液体燃料操作期间，迫使空气横过下游面以冷却头部。有利地，使冷却空气替代环形槽中的先导气体燃料，使其像气体燃料一样被偏转，并与下游面的中心部分接触。燃烧头还具有主要的气体和液体燃料喷射装置，这些装置与附接到头部的径向旋流器中的一个或多个通道连通。

87. 发明授权

US06481209B1 Methods and apparatus for decreasing combustor emissions with swirl stabilized mixer 有权
标题翻译：用旋转稳定混合器减少燃烧器排放的方法和装置
公开(公告)号：US06481209B1
公开(公告)日：2002-11-19
申请号：US09604986
申请日：2000-06-28
申请人： Arthur Wesley Johnson , Robert Andrew Wade , Hukam Chand Mongia , David Louis Burrus
发明人： Arthur Wesley Johnson , Robert Andrew Wade , Hukam Chand Mongia , David Louis Burrus
IPC分类号： F02C7228
CPC分类号： F23R3/346 , F23D2209/20 , F23D2900/00015 , F23R3/16
摘要： A combustor for a gas turbine engine operates with high combustion efficiency, and low carbon monoxide and nitrous oxide emissions during low, intermediate, and high engine power operations. The combustor includes a fuel delivery system that includes at least two fuel stages, at least one trapped vortex cavity, and at least one mixer assembly radially inward from the trapped vortex cavity. The two fuel stages include a pilot fuel circuit that supplies fuel to the trapped vortex cavity through a fuel injector assembly and a main fuel circuit that also supplies fuel to the mixer assembly with the fuel injector assembly.
摘要翻译：用于燃气涡轮发动机的燃烧器以高燃烧效率运行，并且在低，中，高发动机动力运行期间具有低一氧化碳和一氧化二氮排放。燃烧器包括燃料输送系统，其包括至少两个燃料级，至少一个被捕获的涡流空腔和至少一个从被捕获的涡流腔径向向内的混合器组件。两个燃料级包括一个先导燃料回路，该燃料回路通过燃料喷射器组件和主燃料回路将燃料供给到被捕获的涡流空腔，燃料回路还通过燃料喷射器组件向混合器组件提供燃料。

88. 发明授权

US06446439B1 Pre-mix nozzle and full ring fuel distribution system for a gas turbine combustor 有权
标题翻译：用于燃气轮机燃烧器的预混合喷嘴和全环燃料分配系统
公开(公告)号：US06446439B1
公开(公告)日：2002-09-10
申请号：US09706425
申请日：2000-11-03
申请人： Robert J. Kraft , Vincent C. Martling , Brian R. Mack
发明人： Robert J. Kraft , Vincent C. Martling , Brian R. Mack
IPC分类号： F02G100
CPC分类号： F23R3/286 , F23D2900/00008 , F23D2900/00015 , F23R3/343
摘要： A fuel nozzle system for use in a combustor utilized in a combustion turbine for reducing nitrogen oxides and other pollutants including an annular fuel distribution manifold separately mounted away from a diffusion nozzle, said annular manifold having a plurality of fuel emitting passages or holes disposed along the downstream side of the manifold, said manifold being mounted in a position away from the diffuser nozzle body to allow air to stream around the manifold on all sides allowing for a thorough mixture of fuel and air around the annular manifold for better premixing in the combustion chamber. In an alternate embodiment, the diffusion nozzle is replaced by a pilot flame nozzle that is supplied with both air and fuel through a premix air and fuel chamber to a pilot flame nozzle which is used to sustain combustion in the secondary chamber. The use of a pilot flame nozzle that has a fuel and air mixture is believed to reduced NOx emissions.
摘要翻译：一种用于燃烧器中用于还原氮氧化物和其它污染物的燃烧器的燃料喷嘴系统，所述氮氧化物和其它污染物包括分开安装在远离扩散喷嘴的环形燃料分配歧管，所述环形歧管具有多个燃料发射通道歧管的下游侧，所述歧管安装在远离扩散器喷嘴体的位置，以允许空气在所有侧面上的歧管流动，允许在环形歧管周围充分混合燃料和空气，以在燃烧室中更好地预混合。在替代实施例中，扩散喷嘴由引燃火焰喷嘴代替，该引燃火焰喷嘴通过预混合空气和燃料室供应空气和燃料两者到用于维持次级室中的燃烧的引燃火焰喷嘴。使用具有燃料和空气混合物的先导火焰喷嘴被认为减少了NOx排放。

89. 发明申请

US20020011064A1 Fuel injector with bifurcated recirculation zone 审中-公开
标题翻译：具有分叉再循环区域的燃油喷射器
公开(公告)号：US20020011064A1
公开(公告)日：2002-01-31
申请号：US09906544
申请日：2001-07-16
发明人： David S. Crocker , Daniel A. Nickolaus , Clifford E. Smith
IPC分类号： F23R003/14
CPC分类号： F02C7/22 , F05D2270/082 , F23D11/107 , F23D2900/00015 , F23D2900/11101 , F23R3/343 , Y02T50/677
摘要： A gas turbine fuel injection system of the lean direct injector type designed to reduce nitrous oxide (NOx) emissions is provided. The configuration includes a pilot fuel injector for injecting a pilot fuel stream, and a pilot swirler for providing a swirling pilot air stream to atomize and entrain the pilot fuel stream. A main airblast fuel injector is located concentrically about the pilot fuel injector, for injecting a main fuel stream concentrically about the pilot fuel stream. Inner and outer main swirlers provide a swirling main air stream to atomize and entrain the main fuel stream. An air splitter is located between the pilot swirler and the main swirler. The air splitter is so arranged and constructed as to divide the pilot air stream exiting the pilot swirler and the air splitter, from the main air stream exiting the inner main swirler, whereby a bifurcated recirculation zone is created.
摘要翻译：提供了一种设计用于减少一氧化二氮（NOx）排放的稀薄直接喷射器类型的燃气轮机燃料喷射系统。该构造包括用于喷射引燃燃料流的先导燃料喷射器和用于提供旋流先导气流以使雾化和夹带引燃燃料流的先导旋流器。主要的喷气燃料喷射器围绕着先导燃料喷射器同心地定位，用于围绕引燃燃料流同心地喷射主燃料流。内外主旋流器提供旋流的主空气流以雾化和夹带主燃料流。飞行器旋流器和主旋流器之间分布有空分器。空分器被布置和构造成将离开先导旋流器和分流器的先导气流与离开内部主旋流器的主空气流分开，由此产生分叉的再循环区。

90. 发明申请

US20010027637A1 GAS-TURBINE ENGINE COMBUSTION SYSTEM 有权
标题翻译：气涡轮发动机燃烧系统
公开(公告)号：US20010027637A1
公开(公告)日：2001-10-11
申请号：US09240245
申请日：1999-01-29
发明人： ERIC ROY NORSTER , SIMON DEPIETRO , MAHMOUD KOWKABI , HOGER GUNTER HEINRICH HESSE
IPC分类号： F02C009/26
CPC分类号： F23D14/24 , F23C7/002 , F23C2202/40 , F23D14/76 , F23D17/002 , F23D2206/10 , F23D2214/00 , F23D2900/00015 , F23R3/36
摘要： A gas-turbine engine combustion system has a combustor with a burner head having both pilot gas and pilot liquid-fuel injection arrangements, the pilot gas arrangement comprising an annular gallery communicating with a downstream face of the head and a deflecting arrangement adjacent the gallery for directing the pilot gas-fuel towards a longitudinal axis of the combustor and over a central part of the downstream face. The combustion system is designed so that, during both gas- and liquid-fuel operations, the flame front face is located close to the burner head and, during liquid-fuel operation, air is forced across the downstream face to cool the head. Advantageously, the cooling air is made to replace the pilot gas-fuel in the annular gallery, so that it is deflected, like the gas-fuel, and contacts the central part of the downstream face. The burner head also features main gas and liquid-fuel injection arrangements, these communicating with one or more passageways in a radial swirler attached to the head.
摘要翻译：燃气涡轮发动机燃烧系统具有燃烧器，燃烧器头具有先导气体和先导液体 - 燃料喷射装置，所述先导气体装置包括与头部的下游面连通的环形镜片和邻近画廊的偏转装置将先导气体燃料引导到燃烧器的纵向轴线并且在下游面的中心部分上。燃烧系统被设计成使得在气体和液体燃料操作期间，火焰前面靠近燃烧器头部，并且在液体燃料操作期间，迫使空气横过下游面以冷却头部。有利地，使冷却空气替代环形槽中的先导气体燃料，使其像气体燃料一样被偏转，并与下游面的中心部分接触。燃烧头还具有主要的气体和液体燃料喷射装置，这些装置与附接到头部的径向旋流器中的一个或多个通道连通。

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