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1. 发明申请

US20140096502A1 BURNER FOR A GAS TURBINE 审中-公开
标题翻译：燃气轮机
公开(公告)号：US20140096502A1
公开(公告)日：2014-04-10
申请号：US13876250
申请日：2011-09-28
申请人： Andreas Karlsson , Vladimir Dusan Milosavljevic , Magnus Persson
发明人： Andreas Karlsson , Vladimir Dusan Milosavljevic , Magnus Persson
IPC分类号： F02C3/30 , F23R3/14 , F02C7/12 , F23R3/34
CPC分类号： F02C3/30 , F02C7/12 , F23D2900/00014 , F23D2900/00015 , F23D2900/14004 , F23K5/12 , F23R3/14 , F23R3/286 , F23R3/343
摘要： A burner for a gas turbine is provided. The burner has a pilot combustor, a supply module providing pilot fuel and air into a pilot combustion room enclosed by a pilot burner housing having a tapered exit throat discharging radicals and heat generated in a pilot combustion zone into a main combustion room. An equalizer has holes for main flow air entering a cavity in a radial direction with regard to a burner axis defined by centers of pilot combustion zone and main combustion zone. A fuel injector is downstream the equalizer to supply flow fuel into flow air. A swirler is downstream the injector to give flow distribution to the flow fuel and air entering the main combustion room. A channel leads from the equalizer to the swirler arranged circumferentially around the pilot burner housing to direct the main air flow from the equalizer in axial and circumferential direction.
摘要翻译：提供了一种用于燃气轮机的燃烧器。燃烧器具有引燃燃烧器，供给模块向先导燃烧室提供先导燃料和空气，该引燃燃烧室由引燃燃烧器壳体围绕，该引燃燃烧器壳体具有锥形出口喉部，其将在先导燃烧区域中产生的自由基和热量排放到主燃烧室中。相对于由先导燃烧区域和主燃烧区域的中心限定的燃烧器轴线，均衡器具有用于主流动空气沿径向进入空腔的孔。燃料喷射器在均衡器的下游，以将流动燃料供应到流动空气中。旋流器在喷射器的下游，以使得流入燃料和空气进入主燃烧室的流量分配。通道从平衡器引导到围绕导向燃烧器壳体周向布置的旋流器，以引导来自均衡器的主空气流在轴向和圆周方向上。

2. 发明申请

US20140026579A1 BURNER FOR A GAS TURBINE 审中-公开
标题翻译：燃气轮机
公开(公告)号：US20140026579A1
公开(公告)日：2014-01-30
申请号：US13876594
申请日：2011-09-27
申请人： Andreas Karlsson , Magnus Persson
发明人： Andreas Karlsson , Vladimir Dusan Milosavljevic , Magnus Persson
IPC分类号： F23R3/34
CPC分类号： F23R3/343 , F23D2900/00014 , F23D2900/00015 , F23R3/20 , F23R3/286
摘要： A burner for a gas turbine includes a burner housing, and a pilot combustor having a supply module providing pilot fuel and pilot air into a pilot combustion room being enclosed by a pilot combustor housing having a tapered exit with a throat of a defined length into the resulting main flow direction. The throat discharges a concentration of radicals are and heat generated in the pilot combustion room into a main combustion room enclosed by the burner housing. The interior cross section area of the throat deviates from a circle by means of flow guiding elements provided as protrusions with a defined radial height or as recesses with a defined depth extending longitudinally along the direction of the burner axis to give the discharging flow a defined velocity distribution with regard to a circumferential direction.
摘要翻译：一种用于燃气轮机的燃烧器包括燃烧器壳体和引燃燃烧器，其具有向导向燃烧室提供引燃燃料和先导空气的供给模块，该引燃燃烧室由具有限定长度的喉部的具有锥形出口的先导燃烧器壳体包围，主要流向。喉部将先导燃烧室中产生的自由基浓度和热量排放到由燃烧器壳体包围的主燃烧室中。喉部的内部横截面区域通过作为具有限定的径向高度的突起的流动引导元件而偏离圆形，或者具有沿着燃烧器轴线的方向纵向延伸的限定深度的凹部，以使排出流具有限定的速度关于圆周方向的分布。

3. 发明授权

US06539724B2 Airblast fuel atomization system 有权
公开(公告)号：US06539724B2
公开(公告)日：2003-04-01
申请号：US09823149
申请日：2001-03-30
申请人： Michael Dale Cornwell , Anthony William Newman , Vladimir Dusan Milosavljevic
发明人： Michael Dale Cornwell , Anthony William Newman , Vladimir Dusan Milosavljevic
IPC分类号： B05B708
CPC分类号： F23D11/107 , F05B2220/50 , F23D11/103 , F23D11/383
摘要： An airblast fuel injector assembly for use in conjunction with a gas turbine is disclosed which includes an elongated tubular body having first and second concentric tubes separated from one another by a helical spacer wire so as to define a fuel passage therebetween. The injector assembly is situated such that fuel flow exiting the fuel passage is intersected by an air flow at a predetermined angle of incidence so as to atomize the fuel flow.

4. 发明申请

US20140174096A1 METHOD AND ARRANGEMENT FOR INJECTING AN EMULSION INTO A FLAME 审中-公开
标题翻译：将乳剂注入火焰的方法和装置
公开(公告)号：US20140174096A1
公开(公告)日：2014-06-26
申请号：US13825168
申请日：2011-09-20
申请人： Vladimir Dusan Milosavljevic
发明人： Vladimir Dusan Milosavljevic
IPC分类号： F23R3/28 , F23R3/14 , F23R3/34
CPC分类号： F02C3/30 , F23D11/16 , F23D11/38 , F23D2900/11101 , F23K5/12 , F23L7/002 , F23R3/14 , F23R3/286 , F23R3/343 , F23R3/346
摘要： An arrangement for injection of an emulsion of a first fluid and a second fluid into a flame of a burner has a central gas duct, an outer gas channel disposed coaxially with the gas duct, and a fluid channel disposed coaxially between the gas duct and the outer gas channel The central gas duct and the fluid channel are separated by a first frustoconical wall. The fluid channel and the outer gas channel are separated by a second frustoconical wall. The arrangement is mounted concentrically surrounding a heat source which provides through the gas duct hot gases being directed into the flame of the burner. Further, the arrangement includes a mixing device for forming an emulsion of the first fluid and the second fluid, for supplying the emulsion into the fluid channel and for injecting the emulsion from the fluid channel into the flame.
摘要翻译：用于将第一流体和第二流体的乳液注射到燃烧器的火焰中的装置具有中心气体管道，与气体管道同轴设置的外部气体通道，以及同轴地设置在气体管道和外部气体通道中央气体管道和流体通道由第一截头圆锥壁隔开。流体通道和外部气体通道被第二截头圆锥壁隔开。该装置同心地围绕一个热源，该热源通过气体管道提供热气体被引导到燃烧器的火焰中。此外，该装置包括用于形成第一流体和第二流体的乳液的混合装置，用于将乳液供应到流体通道中并将乳液从流体通道注入到火焰中。

5. 发明授权

US07621132B2 Pilot combustor for stabilizing combustion in gas turbine engines 失效
标题翻译：燃气涡轮发动机稳定燃烧的先导燃烧器
公开(公告)号：US07621132B2
公开(公告)日：2009-11-24
申请号：US10933888
申请日：2004-09-03
申请人： Michael Cornwell , Vladimir Dusan Milosavljevic
发明人： Michael Cornwell , Vladimir Dusan Milosavljevic
IPC分类号： F23R3/12
CPC分类号： F23R3/286 , F23R3/343 , Y02E20/344
摘要： The subject application is directed to burners for gas turbine engines that use a pilot flame to assist in sustaining and stabilizing the combustion process. An embodiment of the disclosed burners includes, inter alia, a burner housing, a pilot combustor and a quencher. The burner housing has axially opposed upstream and downstream end portions. Additionally, the housing has at least one main fuel inlet passage and at least one main air inlet passage which are adapted to supply fuel and air respectively to an internal chamber defined in the housing. The pilot combustor is disposed along the axis of the burner housing and has an inlet for receiving a rich fuel and air mixture, a combustion chamber within which the rich fuel and air mixture is combusted into combustion products, and an outlet for exhausting the combustion products from the combustion chamber. The quencher is disposed within the internal chamber of the burner housing along the central axis and positioned at the outlet of the pilot combustor. The quencher has an air inlet and a plurality of radially-oriented air outlets for directing cooling air toward the outlet of the pilot combustor and quenching the combustion products exhausted from the pilot combustor.
摘要翻译：本申请涉及使用引燃火焰辅助维持和稳定燃烧过程的燃气涡轮发动机的燃烧器。所公开的燃烧器的一个实施例尤其包括燃烧器壳体，导向燃烧器和淬火器。燃烧器壳体具有轴向相对的上游和下游端部。此外，壳体具有至少一个主燃料入口通道和至少一个主空气入口通道，其适于将燃料和空气分别供应到限定在壳体中的内部室。导向燃烧器沿着燃烧器壳体的轴线设置，并且具有用于接收富燃料和空气混合物的入口，富燃料和空气混合物燃烧成燃烧产物的燃烧室，以及用于排出燃烧产物的出口从燃烧室。淬火器沿着中心轴线设置在燃烧器壳体的内部腔室内并且定位在引燃燃烧器的出口处。淬火器具有空气入口和多个径向定向的空气出口，用于将冷却空气引导到先导燃烧器的出口并淬火从引燃燃烧器排出的燃烧产物。

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