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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：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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3.发明公开Gas turbine comprising a compressor casing with an inlet opening for tempering the compressor casing and use of the gas turbine 审中-公开燃气涡轮机包括具有用于所述压缩机壳体的温度控制和使用燃气涡轮机的入口开口的压缩机壳体
公开(公告)号：EP2818646A1
公开(公告)日：2014-12-31
申请号：EP13174310.6
申请日：2013-06-28
发明人： Andersson, Thomas , Persson, Allan
CPC分类号： F04D29/584 , F01D11/24 , F01D25/26 , F04D19/00 , F04D29/522 , F05D2260/20
摘要： A gas turbine is provided comprising at least one rotor assembly (10); and at least one compressor casing (11); wherein the compressor casing comprises at least one inner compressor casing chamber (1112) for arranging the rotor assembly and at least one outer compressor casing chamber (1113) for tempering the compressor casing; the inner compressor casing chamber (1112) and the outer compressor casing chamber (1113) are separated from each other by a separating casing wall (1101); the outer compressor casing chamber (1113) comprises at least one boundary casing wall (110); the boundary casing wall (110) and the separating casing wall (1101) are oppositely spaced from each other such that the outer compressor casing chamber is formed; and the boundary casing wall (110) comprises at least one inlet opening (1100) for leading in an inlet tempering gas flow (1115) with tempering gas into the outer compressor casing chamber (1113) such that a tangential material temperature variation of the compressor casing (11) is reduced in comparison to a non tempered compressor casing. Preferably more inlet openings (1100) are distributed alongside an internal surface of the boundary casing wall (110).
摘要翻译： 一种燃气涡轮机提供了一种包括至少一个转子组件（10）; 和至少一个压缩机壳体（11）; worin压缩机壳体用于布置用于回火压缩机壳体的转子组件和至少一个外部压缩机壳体室（1113）包括至少一个内压缩机壳体室（1112）; 内压缩机壳体室（1112）和所述外压缩机壳体室（1113）彼此通过分隔壁壳体（1101）分开; 外压缩机壳体室（1113）包括至少一个边界壁壳体（110）; 边界壁壳体（110）和分离壁壳体（1101）相对地间隔开的从海誓山盟检查做的外压缩机壳体室中形成; 和边界壳体壁（110）包括用于在入口龙头与回火气体到外压缩机壳体室（1113）回火气流（1115）的至少一个入口开口（1100）检查了做了压缩机的切线材料的温度变化 壳体（11）相比于非回火压缩机壳体被降低。 优选地入口开口（1100）被分布在外壳壁边界（110）的内表面并排。
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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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