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1. 发明专利

JP2012042200A Reheat burner 有权
标题翻译： REHEAT燃烧器
公开(公告)号：JP2012042200A
公开(公告)日：2012-03-01
申请号：JP2011175693
申请日：2011-08-11
申请人： Alstom Technology Ltd , アルストムテクノロジーリミテッドALSTOM Technology Ltd
发明人： BUSS JOHANNES , CIANI ANDREA , EROGLU ADNAN , BENZ URS , DUESING MICHAEL , HUTAPEA MICHAEL
IPC分类号： F23R3/20 , F23D14/24 , F23R3/12 , F23R3/18 , F23R3/42
CPC分类号： F23D11/402 , F23D11/408 , F23D14/64 , F23R3/002 , F23R3/12 , F23R3/20 , F23R2900/03341
摘要： PROBLEM TO BE SOLVED: To provide a reheat burner (1) including a channel (2) and a lance (3) projected into the channel to inject fuel over an injection plane (4) perpendicular to a longitudinal axis (15) of the channel.SOLUTION: The channel (2) and the lance (3) define, relative to the flow direction of hot gas (G), a vortex generating zone (6) upstream of the injection plane (4), and a mixing zone (9) downstream of the injection plane (4). The mixing zone (9) has a high speed area (16) with a constant cross section, and a diffusion area (17) with a flared cross section downstream of the high speed area (16) in the flow direction of hot gas (G).
摘要翻译：要解决的问题：为了提供一种包括通道（2）和喷枪（3）的再热燃烧器（1），其突出到通道中以将燃料喷射到垂直于纵向轴线（15）的喷射平面（4）上，的频道。解决方案：通道（2）和喷枪（3）相对于热气（G）的流动方向限定在喷射平面（4）上游的涡流发生区（6），以及混合区（9）在注射平面（4）的下游。混合区（9）具有恒定横截面的高速区域（16）和在高温区域（16）下游的热气体流动方向（G）的扩散区域（17））。版权所有（C）2012，JPO＆INPIT

2. 发明专利

JP2011169582A Combustion device for gas turbine 有权
标题翻译：燃气涡轮机燃烧装置
公开(公告)号：JP2011169582A
公开(公告)日：2011-09-01
申请号：JP2011036247
申请日：2011-02-22
申请人： Alstom Technology Ltd , アルストムテクノロジーリミテッドALSTOM Technology Ltd
发明人： HUBER ANDREAS , NICOLAS NOIRAY , BENZ URS , REINERT FELIX , LAUFFER DIANE
IPC分类号： F23R3/42 , F23R3/18
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014
摘要： PROBLEM TO BE SOLVED: To provide a combustion device wherein a smaller air mass flow rate is made to flow from a plenum to decay volume. SOLUTION: The combustion device 1 for a gas turbine comprises a portion 6 including an inner wall 7 and an outer wall 8. The inner wall 7 comprises first passages 9 connecting a zone between the inner and outer walls 7, 8 to the inner side 10 of the combustion device 1. The outer wall 8 comprises second passages 2 for cooling the inner wall 7. Between the inner and outer walls 7, 8, an intermediate layer 17 is provided defining a plurality of chambers 18, each connected to at least one first passage 9 and the plurality of second passages 12 and defining Helmholtz dampers. The second passages 12 open in third passages 22 connected to the chambers 18 and have outlets 23 facing to each other. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种燃烧装置，其中使得较小的空气质量流量从充气室流动至衰减体积。解决方案：用于燃气轮机的燃烧装置1包括包括内壁7和外壁8的部分6.内壁7包括将内壁7和外壁8之间的区域连接到第一通道9的第一通道9 外壁8包括用于冷却内壁7的第二通道2。在内壁7和外壁8之间设置有中间层17，其限定多个室18，每个室18连接到至少一个第一通道9和多个第二通道12，并限定亥姆霍兹阻尼器。第二通道12在连接到腔室18的第三通道22中打开并且具有彼此面对的出口23。版权所有（C）2011，JPO＆INPIT

3. 发明专利

JP2010216481A Gas turbine burner and method for partially cooling hot gas flow passing through burner 有权
标题翻译：燃气轮机燃烧器和部分冷却通过燃烧器通入热气的方法
公开(公告)号：JP2010216481A
公开(公告)日：2010-09-30
申请号：JP2010056982
申请日：2010-03-15
申请人： Alstom Technology Ltd , アルストムテクノロジーリミテッドALSTOM Technology Ltd
发明人： EROGLU ADNAN , CIANI ANDREA , BUSS JOHANNES , DUESING MICHAEL , BENZ URS
IPC分类号： F02C7/18 , F23R3/10 , F23R3/16 , F23R3/32
CPC分类号： F02C6/003 , F05D2240/127 , F05D2250/21 , F23D2209/20 , F23R3/06 , F23R3/16 , F23R3/18
摘要： PROBLEM TO BE SOLVED: To provide a burner and a method for reducing the risk of flashback. SOLUTION: This burner (1) for a gas turbine includes a plurality of swirl generators (3) of tetrahedral shape and a lance (4) for injecting a fuel to be burned. The plurality of swirl generators (3) in a duct (2) includes a plurality of cooling holes (9). The cooling holes (9) form passing areas which are nonuniformly disposed on the upper walls (11) of the swirl generators (3). This invention also relates to a method for partially cooling the hot gas flow passing through the burner. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供燃烧器和降低回火风险的方法。解决方案：用于燃气轮机的燃烧器（1）包括多个四面体形状的涡流发生器（3）和用于喷射要燃烧的燃料的喷枪（4）。管道（2）中的多个涡流发生器（3）包括多个冷却孔（9）。冷却孔（9）形成不均匀地设置在涡流发生器（3）的上壁（11）上的通过区域。本发明还涉及一种部分冷却通过燃烧器的热气流的方法。版权所有（C）2010，JPO＆INPIT

4. 发明专利

JP2012063134A Fuel lance used for gas turbine plant and method for operating fuel lance 有权
标题翻译：用于气体涡轮机的燃油和操作燃油的方法
公开(公告)号：JP2012063134A
公开(公告)日：2012-03-29
申请号：JP2011258111
申请日：2011-11-25
申请人： Alstom Technology Ltd , アルストムテクノロジーリミテッドALSTOM Technology Ltd
发明人： EROGLU ADNAM , GUETHE FELIX , BENZ URS
IPC分类号： F23R3/28 , F02C3/14 , F02C3/30 , F02C7/232 , F23R3/36
CPC分类号： F23R3/36 , F23L7/00 , F23L2900/07002 , F23L2900/07009 , Y02E20/16
摘要： PROBLEM TO BE SOLVED: To enable the use of syngas as fuel in the second combustion stage of a staged combustion type gas turbine, without significant modifications in the outside dimensions.SOLUTION: A lance part of a fuel lance 25 used for a staged combustion type gas turbine plant 10, extending in the direction of a flow of hot gas 37, includes: at least one outer tube 26 arranged concentrically to a lance axis 34; and an intermediate tube 27 arranged concentrically in the outer tube 26. In the intermediate tube 27, the fuel 29 is directed to a lance tip part 38 and is sprayed into the hot gas 37 through first spray openings 28 in the region of the lance tip part 38. The first spray openings 28 are arranged directly at the lance tip part 38, and the first spray openings 28 are oriented in such a way that the fuel jets flowing out from the first spray openings 28 form an acute angle with the lance axis 34.
摘要翻译：要解决的问题：为了能够在分级燃烧式燃气轮机的第二燃烧阶段中使用合成气作为燃料，而在外部尺寸上没有显着的修改。解决方案：用于分段燃烧式燃气轮机设备10的燃料喷枪25的喷枪部分，其沿热气37的流动方向延伸，包括：至少一个外管26，其与喷枪轴线同心地布置 34; 以及同心地设置在外管26中的中间管27.在中间管27中，燃料29被引导到喷枪尖部38，并且通过喷枪尖端的区域中的第一喷射开口28喷射到热气体37中第一喷射开口28直接布置在喷枪尖部分38处，并且第一喷射开口28被定向成使得从第一喷射开口28流出的燃料射流与喷枪轴线形成锐角 34.版权所有（C）2012，JPO＆INPIT

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