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公开(公告)号：EP3564585A1
公开(公告)日：2019-11-06
申请号：EP18170798.5
申请日：2018-05-04
摘要： The present invention relates to a swirler arrangement (10; 10a) of a burner (52), in particular of a gas turbine engine (14), comprising at least two wings (16, 18; 16a, 18a), wherein a thread-like flow channel (20) is arranged between the at least two wings (16, 18; 16a, 18a), wherein the flow channel (20) is allowing a flow medium (22) to travel along the flow channel (20) in a flow direction (24, 24') and wherein the flow medium (22) is set into a thread-like motion by the flow channel (20) when flowing through the flow channel (20) and wherein each wing (16, 18; 16a, 18a) of the at least two wings (16, 18; 16a, 18a) comprise an upstream part (26) and a downstream part (28; 28a).
To increase the flashback resistance of the burner (52) it is proposed that the downstream part (28; 28a) comprises at least one opening (30; 30a) for injecting fuel (32) into the flow medium (22) while traveling the flow channel (20).-
公开(公告)号：EP3637000A1
公开(公告)日：2020-04-15
申请号：EP18199840.2
申请日：2018-10-11
摘要： The invention relates to a burner (1) for a gas turbine with a supply zone (2) for supplying fuel and air and a subsequent mixing zone (3) for premixing fuel and air, the mixing zone (3) having an upstream end (4) and a downstream end (5) and comprising a plurality of premix jet pipes (6) for mixing air and fuel, each with an inlet (7) and an outlet (8), arranged around a central burner axis (9) and extending between the upstream end (4) and the downstream end (5), wherein closer to the upstream end (4) the premix jet pipes (6) are straight and parallel to each other and wherein closer to the downstream end (5) the premix jet pipes (6) are bent away from the central burner axis (9) wherein a bending of the premix jet pipes (6) increases with the distance between premix jet pipe (6) and central burner axis (9), wherein a diameter (11) of the premix jet pipes (6) is between 0.5 mm and 10 mm.
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公开(公告)号：EP2107301A1
公开(公告)日：2009-10-07
申请号：EP08006659.0
申请日：2008-04-01
CPC分类号： F23C7/004 , F23C2900/07001 , F23D14/02 , F23D14/58 , F23D14/70 , F23D2900/14003 , F23D2900/14701 , F23R3/286
摘要： The invention relates to a gas injector for injecting fuel into a burner for a gas turbine engine.
It is an object of the present invention to improve the mixing efficiency of air and fuel to further enhance the efficiency of a burner. According to the invention the gas injector comprises a burner (1) provided with a quarl (4a, 4b, 4c), which is circumferenting a combustion room, at least a first channel (10, 11) emerging into the combustion room for providing the combustion room with air (12) mixed with fuel (14); a swirler (3) for mixing the air (12) and the fuel (14) located at the inlet of said channel (10, 11); at least one tube (15) for the provision of fuel (14) at an inlet (13) of at least one channel (10, 11), wherein said tube (15) is provided with a plurality of diffuser holes (15A) distributed along the tube (15) acting as gas injectors for effectively distributing fuel (14) in a flow of air passing through said channel (10, 11).摘要翻译： 本发明涉及一种用于将燃料喷射到用于燃气涡轮发动机的燃烧器中的气体喷射器。 本发明的目的是提高空气和燃料的混合效率，以进一步提高燃烧器的效率。 根据本发明，气体喷射器包括燃烧器（1），燃烧器（1）设置有四周（4a，4b，4c），其围绕燃烧室，至少一个出现在燃烧室中的第一通道（10,11），用于提供 燃烧室与空气（12）混合燃料（14）; 用于混合空气（12）和位于所述通道（10,11）的入口处的燃料（14）的旋流器（3）; 至少一个用于在至少一个通道（10,11）的入口（13）处提供燃料（14）的管（15），其中所述管（15）设置有多个分配的扩散器孔（15A） 沿着作为气体喷射器的管（15），用于在通过所述通道（10,11）的空气流中有效地分配燃料（14）。
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公开(公告)号：EP2107301B1
公开(公告)日：2016-01-06
申请号：EP08006659.0
申请日：2008-04-01
CPC分类号： F23C7/004 , F23C2900/07001 , F23D14/02 , F23D14/58 , F23D14/70 , F23D2900/14003 , F23D2900/14701 , F23R3/286
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公开(公告)号：EP2110601A1
公开(公告)日：2009-10-21
申请号：EP08007392.7
申请日：2008-04-15
发明人： Andersson, Henrik , Brodin, Haakan , Gao, Xiufang , Persson, Magnus , Vujicic, Zeljko , Österlund, Patric
CPC分类号： F23D14/02 , F23D11/103 , F23D14/82 , F23D2209/10 , F23D2900/14003 , F23D2900/14021 , F23D2900/14701 , F23R3/286 , F23R3/343
摘要： A burner with a burner head comprises a mixing tube (3) for premixing combustion air and fuel. The mixing tube (3) is provided with a pilot burner system in its downstream part. The pilot burner system comprises an annular mixing cavity (10) with an entrance for assist air and pilot fuel and with outlet nozzles (7). The mixing cavity (10) is provided with at least two swirler wings (18) being arranged in the vicinity of each outlet nozzle (7).
摘要翻译： 具有燃烧头的燃烧器包括用于预混燃烧空气和燃料的混合管（3）。 混合管（3）在其下游部分设有引燃燃烧器系统。 引燃燃烧器系统包括具有辅助空气和引燃燃料入口的入口喷嘴（7）的环形混合腔（10）。 混合腔（10）设置有至少两个在每个出口喷嘴（7）附近布置的旋流器翼（18）。
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公开(公告)号：EP3517757A1
公开(公告)日：2019-07-31
申请号：EP18154122.8
申请日：2018-01-30
摘要： The invention relates to a method for operating a power device (1), the power device (1) comprises a gas turbine (2) and an exhaust gas system (3) for treatment of exhaust gas, wherein the gas turbine (2) comprises a combustion chamber (5) and a turbine (6), the gas turbine (2) is at least configured for co-firing hydrogen and/or ammonia, wherein the hydrogen and/or the ammonia is supplied by an ammonia system (8), comprising the steps of:
a) providing the ammonia in the ammonia system (8),
b) heating the ammonia in the ammonia system (8) with heat from the power device (1) to decompose the ammonia completely or partly into nitrogen and hydrogen,
c) injecting at least the hydrogen and/or the nitrogen, and/or the remaining ammonia into the combustion chamber (5) of the gas turbine (2),
d) combusting at least the hydrogen and/or the nitrogen, and/or the remaining ammonia in the combustion chamber (5) of the gas turbine (2),
e) treating the exhaust gas of the combustion chamber (5) with ammonia from the ammonia system (8) to remove at least nitrogen oxides from the exhaust gas of the combustion chamber (5).-
7.发明公开A PREMIXED DUAL FUEL BURNER WITH A TAPERING INJECTION COMPONENT FOR MAIN LIQUID FUEL 审中-公开VORGEMISCHTER DUALER BRENNSTOFFBRENNER MIT SICHVERSCHMÄLERNDEREINSPRITZKOMPONENTEFÜRDENHAUPTFLÜSSIGBRENNSTOFF
公开(公告)号：EP3133342A1
公开(公告)日：2017-02-22
申请号：EP15181707.9
申请日：2015-08-20
CPC分类号： F23C1/08 , F23C2900/07001 , F23C2900/07002 , F23C2900/07021 , F23D11/402 , F23R3/14 , F23R3/286
摘要： A premixed dual fuel burner includes a burner head, a burner interior elongated along a main axis and having an upstream side enclosed by a swirler and a downstream side enclosed by a premixing section, and an injection component. The burner head, the upstream side and the downstream side are serially arranged. The swirler includes an inlet section for introducing air and a main gas fuel into the burner interior. The injection component has a tapering structure positioned along the main axis. The tapering structure extends from the burner head into the burner interior. The injection component has a burner head side and an injection side and tapers from the burner head side to the injection side along the main axis. At the injection side a liquid fuel outlet is present for introducing a main liquid fuel into the burner interior. The injection side is disposed in the burner interior.
摘要翻译： 预混合双燃料燃烧器包括燃烧器头部，沿主轴线延伸的燃烧器内部并具有由旋流器封闭的上游侧和由预混合部分包围的下游侧以及注射部件。 燃烧器头部，上游侧和下游侧连续排列。 旋流器包括用于将空气和主气体燃料引入燃烧器内部的入口部分。 注射部件具有沿主轴定位的锥形结构。 锥形结构从燃烧头延伸到燃烧器内部。 注射部件具有燃烧器头侧和注射侧，并且沿着主轴从燃烧器头侧朝向注射侧逐渐变细。 在注射侧，存在用于将主液体燃料引入燃烧器内部的液体燃料出口。 注射侧设置在燃烧器内部。
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公开(公告)号：EP2767696A1
公开(公告)日：2014-08-20
申请号：EP13155455.2
申请日：2013-02-15
CPC分类号： F02C1/05 , F02C1/06 , F02C3/04 , F02C7/222 , F02C7/224 , F03G6/064 , F05D2220/32 , F05D2240/35 , F23R3/005 , F23R3/28 , F23R3/343 , Y02E10/46
摘要： The invention relates to an assembly (AS) comprising a gas turbine (GT) and a heat exchanger (HE) for heating up a gas turbine process fluid (GTPF) by thermal energy , said gas turbine (GT) comprising a compressor (CO), a combustor (CB) and a turbine (TB) downstream said combustor (CB), characterized by thermal energy from said solar receiver (SR). To improve efficiency and reduce power generation fluctuations it is proposed that said assembly (AS) comprises:
- a first line (L1) to conduct said gas turbine process fluid (GTPF) downstream a compression by said compressor (CO) to said heat exchanger (HE),
- a second line (L2) to conduct said gas turbine process fluid (GTPF) from said heat exchanger (HE) to said combustor (CB) to generate hot combustion gas (HCG) from said warmed up gas turbine process fluid (GTPF) burning fuel (F) in said combustor (CB).摘要翻译： 本发明涉及一种包括燃气轮机（GT）和用于通过热能加热燃气轮机过程流体（GTPF）的热交换器（HE）的组件（AS），所述燃气轮机（GT）包括压缩机（CO） ，在燃烧器（CB）下游的燃烧器（CB）和涡轮机（TB），其特征在于来自所述太阳能接收器（SR）的热能。 为了提高效率并减少发电波动，提出所述组件（AS）包括： - 第一管线（L1），用于将所述压缩机（CO）压缩到所述热交换器（CO）的下游的所述燃气轮机过程流体（GTPF） HE）， - 将所述燃气轮机过程流体（GTPF）从所述热交换器（HE）传导到所述燃烧器（CB）的第二管线（L2），以从所述预热燃气轮机过程流体（ GTPF）在燃烧器（CB）中燃烧燃料（F）。
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公开(公告)号：EP2436979A1
公开(公告)日：2012-04-04
申请号：EP10184357.1
申请日：2010-09-30
CPC分类号： F02C3/30 , F02C7/12 , F23D2900/00014 , F23D2900/00015 , F23D2900/14004 , F23K5/12 , F23R3/14 , F23R3/286 , F23R3/343
摘要： The invention relates to a burner (1) for a gas turbine, comprising a pilot combustor (5), a supply module providing pilot fuel (20) and pilot air (21) into a pilot combustion room (23) being enclosed by a pilot burner housing (22) comprising a tapered exit throat (24) discharging a concentration of radicals and heat generated in a pilot combustion zone (25) into a main combustion room (15) enclosed by a burner housing (4). Further said burner (1) comprises an equalizer (6), which is provided with a plurality of holes through which a main flow of air (7) enters a cavity (8), wherein said burner further comprises a fuel injector (9) downstream the equalizer (6) to supply a main flow of fuel (12) into the main flow of air (7), wherein a burner axis (3) is defined by the center of the pilot combustion zone (23) and the center of the main combustion zone (14), wherein said burner further comprises a swirler (13) downstream the injector (9) to give a designated flow distribution to the flow of fuel (12) and air (7) entering downstream said main combustion room (15). To mainly reduce space requirement the equalizer (6) is built in such a manner that the main air (7) flow enters the cavity (8) in a basically radial direction with regard to the burner axis (3), wherein a channel leads from the equalizer (6) to the swirler (13) arranged circumferentially around the pilot burner housing (22), said channel and said swirler being built in such a way that the main air flow (7) from said equalizer is directed in a basically axial and circumferential direction.
摘要翻译： 本发明涉及一种用于燃气轮机的燃烧器（1），其包括先导燃烧室（5），将先导燃料（20）和先导空气（21）提供到先导燃烧室（23）中的供给模块，所述先导燃烧室（23） 燃烧器壳体（22）包括锥形出口喉部（24），其将在先导燃烧区域（25）中产生的自由基和热量的浓缩物排放到由燃烧器壳体（4）包围的主燃烧室（15）中。 进一步地，所述燃烧器（1）包括均衡器（6），所述均衡器设置有多个孔，主流气流（7）通过所述多个孔进入空腔（8），其中所述燃烧器还包括下游的燃料喷射器 所述均衡器（6）将主燃料流（12）供应到所述主空气流（7）中，其中燃烧器轴线（3）由所述引燃燃烧区（23）的中心和所述 主燃烧区（14），其中所述燃烧器还包括位于所述喷射器（9）下游的旋流器（13），以向进入所述主燃烧室（15）下游的燃料流（12）和空气（7） ）。 为了主要减小空间需求，平衡器6以这样的方式构造，使得主空气7流体相对于燃烧器轴线3基本上沿径向方向进入空腔8，其中通道从 （22）周围布置的平衡器（6）到旋流器（13），所述通道和所述旋流器以这样的方式构建，使得来自所述均衡器的主空气流（7）基本上轴向地 和圆周方向。
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公开(公告)号：EP2107300A1
公开(公告)日：2009-10-07
申请号：EP08006658.2
申请日：2008-04-01
CPC分类号： F23C7/004 , F23C2900/07001 , F23D14/02 , F23D14/70 , F23D2900/14021 , F23R3/14 , F23R3/286
摘要： The invention relates to a swirler for premixing a flow of fuel (14) and a flow of air (12) provided to a burner (1) for a gas turbine engine, which burner (1) is provided with a swirler (3) for mixing the air (12) and the fuel (14) and wherein the swirler (3) is provided with swirler wings (3a), wherein a channel formed between two adjacent swirler wings (3a) defines a passage. It is one object of the invention to provide stability to a lean premixed combustion. This is achieved by a swirler of the above mentioned type having one fuel tube (15) for gaseous fuel positioned in parallel on each side of a mixing rod (15b) in said passage, wherein said fuel tubes (15) are provided with a plurality of diffuser holes (15a) distributed along the tube (15) acting as gas injectors for efficiently distributing fuel (14) in a flow of air passing through said swirler (3) passage.
摘要翻译： 本发明涉及一种用于将燃料流（14）和设置到燃气涡轮发动机的燃烧器（1）的空气流（12）进行预混的旋流器，该燃烧器（1）设置有旋流器（3），用于 混合空气（12）和燃料（14），并且其中旋流器（3）设置有旋流器翼（3a），其中形成在两个相邻的旋流器翼（3a）之间的通道限定通道。 本发明的一个目的是提供对预混燃烧的稳定性。 这是通过上述类型的旋流器实现的，其具有一个用于在所述通道中的混合杆（15b）的每一侧平行布置的用于气体燃料的燃料管（15），其中所述燃料管（15）设置有多个 沿着管（15）分布的作为气体喷射器的扩散孔（15a），用于在通过所述旋流器（3）通道的空气流中有效地分配燃料（14）。
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