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1. 发明授权

US08511059B2 Methods of reducing emissions for a sequential combustion gas turbine and combustor for a gas turbine 有权
标题翻译：减少用于燃气轮机的顺序燃烧燃气轮机和燃烧器的排放的方法
公开(公告)号：US08511059B2
公开(公告)日：2013-08-20
申请号：US12241211
申请日：2008-09-30
申请人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Richard Carroni , Gregory John Kelsall , Jian-Xin Chen
发明人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Richard Carroni , Gregory John Kelsall , Jian-Xin Chen
IPC分类号： F02C1/06 , F02C6/00
CPC分类号： F23R3/346
摘要： In an SEV combustor and a method for reducing emissions in an SEV combustor of a sequential combustion gas turbine, an air/fuel mixture is combusted in a first burner and the hot gases are subsequently introduced into the SEV combustor (1) for further combustion. The SEV combustor (1) includes a chamber having a chamber wall (5) defining a mixing portion (8), for mixing the hot gases with a fuel, and a combustion region (9), at least one inlet (2) for introducing the hot gases into the mixing region (8), at least one inlet (12) for introducing a fuel into the mixing region (8) and at least one inlet (10, 13) for introducing steam into the mixing region.
摘要翻译：在SEV燃烧器和用于减少顺序燃烧燃气轮机的SEV燃烧器中的排放的方法中，空气/燃料混合物在第一燃烧器中燃烧，并且随后将热气体引入到SEV燃烧器（1）中以进一步燃烧。 SEV燃烧器（1）包括具有限定混合部分（8）的室壁（5）的室，用于将热气体与燃料混合，以及燃烧区域（9），至少一个入口（2），用于引入进入混合区域（8）的热气体，用于将燃料引入混合区域（8）的至少一个入口（12）和用于将蒸汽引入混合区域的至少一个入口（10,13）。

2. 发明授权

US08220271B2 Fuel lance for a gas turbine engine including outer helical grooves 有权
标题翻译：用于包括外螺旋槽的燃气涡轮发动机的燃料喷枪
公开(公告)号：US08220271B2
公开(公告)日：2012-07-17
申请号：US12241223
申请日：2008-09-30
申请人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Gregory John Kelsall
发明人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Gregory John Kelsall
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/28 , F23C2900/07021 , F23C2900/99011 , F23R2900/03341
摘要： A fuel lance (7) for introducing fuel into a gas flow in a combustor (1) of a gas turbine engine includes a region of the lance (7) through which the fuel is introduced into the gas flow having a generally helical formation (12).
摘要翻译：用于将燃料引入燃气涡轮发动机的燃烧器（1）中的气体流的燃料喷枪（7）包括喷枪（7）的区域，燃料通过所述区域被引入具有大致螺旋形状的气流（12 ）。

3. 发明申请

US20100077756A1 FUEL LANCE FOR A GAS TURBINE ENGINE 有权
标题翻译：燃气涡轮发动机燃油
公开(公告)号：US20100077756A1
公开(公告)日：2010-04-01
申请号：US12241223
申请日：2008-09-30
申请人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Gregory John Kelsall
发明人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Gregory John Kelsall
IPC分类号： F02C7/22 , F23R3/28
CPC分类号： F23R3/28 , F23C2900/07021 , F23C2900/99011 , F23R2900/03341
摘要： A fuel lance (7) for introducing fuel into a gas flow in a combustor (1) of a gas turbine engine includes a region of the lance (7) through which the fuel is introduced into the gas flow having a generally helical formation (12).
摘要翻译：用于将燃料引入燃气涡轮发动机的燃烧器（1）中的气体流的燃料喷枪（7）包括喷枪（7）的区域，燃料通过所述区域被引入具有大致螺旋形状的气流（12 ）。

4. 发明申请

US20100077720A1 METHODS OF REDUCING EMISSIONS FOR A SEQUENTIAL COMBUSTION GAS TURBINE AND COMBUSTOR FOR A GAS TURBINE 有权
标题翻译：用于燃气涡轮机的排气燃料和燃烧器排放的方法
公开(公告)号：US20100077720A1
公开(公告)日：2010-04-01
申请号：US12241211
申请日：2008-09-30
申请人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Richard Carroni , Gregory John Kelsall , Jian-Xin Chen
发明人： Madhavan Narasimhan Poyyapakkam , Adnan Eroglu , Richard Carroni , Gregory John Kelsall , Jian-Xin Chen
IPC分类号： F02C3/30
CPC分类号： F23R3/346
摘要： In an SEV combustor and a method for reducing emissions in an SEV combustor of a sequential combustion gas turbine, an air/fuel mixture is combusted in a first burner and the hot gases are subsequently introduced into the SEV combustor (1) for further combustion. The SEV combustor (1) includes a chamber having a chamber wall (5) defining a mixing portion (8), for mixing the hot gases with a fuel, and a combustion region (9), at least one inlet (2) for introducing the hot gases into the mixing region (8), at least one inlet (12) for introducing a fuel into the mixing region (8) and at least one inlet (10, 13) for introducing steam into the mixing region.
摘要翻译：在SEV燃烧器和用于减少顺序燃烧燃气轮机的SEV燃烧器中的排放的方法中，空气/燃料混合物在第一燃烧器中燃烧，并且随后将热气体引入到SEV燃烧器（1）中以进一步燃烧。 SEV燃烧器（1）包括具有限定混合部分（8）的室壁（5）的室，用于将热气体与燃料混合，以及燃烧区域（9），至少一个入口（2），用于引入进入混合区域（8）的热气体，用于将燃料引入混合区域（8）的至少一个入口（12）和用于将蒸汽引入混合区域的至少一个入口（10,13）。

5. 发明授权

US07878002B2 Methods and systems to facilitate reducing combustor pressure drops 有权
标题翻译：有助于减少燃烧器压降的方法和系统
公开(公告)号：US07878002B2
公开(公告)日：2011-02-01
申请号：US11787671
申请日：2007-04-17
申请人： Madhavan Narasimhan Poyyapakkam
发明人： Madhavan Narasimhan Poyyapakkam
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/08 , F23R3/54 , Y10T29/4932
摘要： A method for assembling a gas turbine combustor includes providing a combustor case having a first end, a second end, and a centerline extending there between, coupling an end cover to the case first end, coupling a combustor liner within the case such that the liner is substantially coaxially aligned with respect to the case, and providing a streamline flow conditioner including a body that includes a radially outer surface and a radially inner surface, a deflection plate that extends from the body, and coupling the streamline flow conditioner to the case second end such that the streamline flow conditioner is coupled radially between the case and the combustor liner such that the deflection plate is adjacent the case second end. The deflection plate inner surface at least one of extends radially outward with respect to the centerline and defines a plurality of openings within the plate inner surface.
摘要翻译：一种用于组装燃气轮机燃烧器的方法包括提供具有第一端，第二端和在其间延伸的中心线的燃烧器壳体，其将端盖连接到壳体的第一端部，将燃烧器衬套连接到壳体内，使得衬套相对于壳体基本上同轴对准，并且提供包括主体的流线型流动调节器，该主体包括径向外表面和径向内表面，偏转板从主体延伸，并将流线型流动调节器联接到壳体秒使得流线型流动调节器径向耦合在壳体和燃烧器衬套之间，使得偏转板与壳体的第二端相邻。偏转板内表面中的至少一个相对于中心线径向向外延伸并且在板内表面内限定多个开口。

6. 发明授权

US08528313B2 Burner for a second chamber of a gas turbine plant 有权
标题翻译：第二个燃气轮机厂的燃烧器
公开(公告)号：US08528313B2
公开(公告)日：2013-09-10
申请号：US12437286
申请日：2009-05-07
申请人： Richard Carroni , Madhavan Narasimhan Poyyapakkam , Michal Bialkowski , Mark Andrew Willetts
发明人： Richard Carroni , Madhavan Narasimhan Poyyapakkam , Michal Bialkowski , Mark Andrew Willetts
IPC分类号： F02C3/14
CPC分类号： F23D14/64 , F23C2900/07001 , F23D2900/14004 , F23D2900/14021 , F23R3/286
摘要： The present invention relates to a burner for a combustion chamber of a gas turbine plant, with an injection device for introducing gaseous fuel into the burner. The injection device has a body which is arranged in the burner and which has at least one nozzle for introducing gaseous fuel into the burner. The body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction transversely with respect to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at an trailing edge of the streamlined body.
摘要翻译：本发明涉及一种用于燃气轮机设备的燃烧室的燃烧器，其具有用于将气态燃料引入燃烧器的注射装置。注射装置具有布置在燃烧器中并具有至少一个用于将气体燃料引入燃烧器的喷嘴的主体。主体构造成流线型的主体，其具有流线型的横截面轮廓，并且其纵向方向相对于燃烧器中主要的主流动横向方向延伸。至少一个喷嘴在其流线型主体的后缘具有其出口孔。

7. 发明申请

US20100077757A1 COMBUSTOR FOR A GAS TURBINE ENGINE 有权
标题翻译：燃气轮机发动机
公开(公告)号：US20100077757A1
公开(公告)日：2010-04-01
申请号：US12241199
申请日：2008-09-30
申请人： Madhavan Narasimhan Poyyapakkam
发明人： Madhavan Narasimhan Poyyapakkam
IPC分类号： F02C1/00
CPC分类号： F23C6/04 , F23C2201/401 , F23C2900/06041 , F23C2900/07002 , F23M9/10 , F23R3/00 , F23R3/346 , F23R2900/03041 , F23R2900/03341
摘要： A combustor (1) for a gas turbine engine, particularly for a gas turbine having sequential combustion, includes a combustor wall (4) defining a mixing region (5) and a combustion region (6). The mixing region (5) has at least one first inlet (2) for introducing combustion air into the mixing region (5) and at least one second inlet for introducing fuel into the mixing region (5), the combustion region (6) extending downstream of the mixing region. The mixing region (5) crosses over to the combustion region (6) in a transition region (14). A baffle (9) extends from the transition region (14) generally in the downstream direction (15), forming at least one space (10) between the combustor wall (4) and the baffle (9).
摘要翻译：用于燃气涡轮发动机的燃烧器（1），特别是具有顺序燃烧的燃气轮机，包括限定混合区域（5）和燃烧区域（6）的燃烧器壁（4）。混合区域（5）具有用于将燃烧空气引入混合区域（5）的至少一个第一入口（2）和用于将燃料引入混合区域（5）的至少一个第二入口，燃烧区域（6）延伸在混合区域的下游。混合区域（5）在过渡区域（14）中与燃烧区域（6）交叉。挡板9通常沿下游方向（15）从过渡区域（14）延伸，在燃烧器壁（4）和挡板（9）之间形成至少一个空间（10）。

8. 发明授权

US09347663B2 Swirler having vanes provided with at least two lobes in opposite transverse directions with reference to a vane central plane 有权
标题翻译：旋流器具有相对于叶片中心平面在相对横向方向上设置有至少两个叶片的叶片
公开(公告)号：US09347663B2
公开(公告)日：2016-05-24
申请号：US13470109
申请日：2012-05-11
申请人： Madhavan Narasimhan Poyyapakkam , Fernando Biagioli , Khawar Syed , Ronghai Mao , Stefano Bernero
发明人： Madhavan Narasimhan Poyyapakkam , Fernando Biagioli , Khawar Syed , Ronghai Mao , Stefano Bernero
IPC分类号： F23R3/14 , F23C7/00
CPC分类号： F23C7/004 , F23D2900/14004 , F23D2900/14021 , F23R3/14 , Y10T137/2087
摘要： A swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler. The leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions. A burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.
摘要翻译：旋流器包括具有限制壁的环形壳体。至少两个叶片布置在环形壳体中，包括旋流器的侧壁。每个叶片的前缘区域具有平行于在前缘位置处的主流动方向定向的轮廓，其中叶片的轮廓从主流动方向转动，以在前缘位置上施加漩涡，流动，并且其中，参考叶片的中心平面，后缘在相对的横向方向上设置有至少两个叶片。一种燃气轮机的燃烧室的燃烧器，包括这种旋流器和至少一个喷嘴，其具有位于叶片的后缘处或其后缘处的出口孔以及这种燃烧器的操作方法。

9. 发明授权

US08938971B2 Flow straightener and mixer 有权
标题翻译：流量矫直机和搅拌机
公开(公告)号：US08938971B2
公开(公告)日：2015-01-27
申请号：US13469819
申请日：2012-05-11
申请人： Madhavan Narasimhan Poyyapakkam , Khawar Syed , Satish Kumar Gajula , John Philip Wood
发明人： Madhavan Narasimhan Poyyapakkam , Khawar Syed , Satish Kumar Gajula , John Philip Wood
IPC分类号： F02K1/00 , B64D33/04 , F23R3/34 , B01F5/04 , B01F5/06 , F23D14/62 , F23R3/18 , F23R3/20 , F23R3/28
CPC分类号： F23R3/34 , B01F5/0451 , B01F5/0456 , B01F5/0463 , B01F5/0616 , F23D14/62 , F23R3/18 , F23R3/20 , F23R3/286 , F23R2900/03341
摘要： A combined flow straightener and mixer is disclosed as well as a burner for a combustion chamber of a gas turbine having such a mixing device. At least two streamlined bodies are arranged in a structure comprising the side walls of the mixer. The leading edge area of each streamlined body has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, and with reference to a central plane of the streamlined bodies, the trailing edges are provided with at least two lobes in opposite transverse directions. The periodic deflections forming the lobes from two adjacent streamlined bodies are out of phase.
摘要翻译：公开了一种组合式矫直机和混合器，以及具有这种混合装置的燃气轮机的燃烧室的燃烧器。至少两个流线型的主体被布置在包括混合器的侧壁的结构中。每个流线型主体的前缘区域具有平行于在前缘位置上的主流动方向定向的轮廓，并且参考流线型本体的中心平面，后缘设置有至少两个凸角在相反的横向。形成来自两个相邻流线型体的裂片的周期性偏转异相。

10. 发明申请

US20080256956A1 Methods and systems to facilitate reducing combustor pressure drops 有权
标题翻译：有助于减少燃烧器压降的方法和系统
公开(公告)号：US20080256956A1
公开(公告)日：2008-10-23
申请号：US11787671
申请日：2007-04-17
申请人： Madhavan Narasimhan Poyyapakkam
发明人： Madhavan Narasimhan Poyyapakkam
IPC分类号： F23R3/04 , B23P15/04
CPC分类号： F23R3/08 , F23R3/54 , Y10T29/4932
摘要： A method for assembling a gas turbine combustor includes providing a combustor case having a first end, a second end, and a centerline extending there between, coupling an end cover to the case first end, coupling a combustor liner within the case such that the liner is substantially coaxially aligned with respect to the case, and providing a streamline flow conditioner including a body that includes a radially outer surface and a radially inner surface, a deflection plate that extends from the body, and coupling the streamline flow conditioner to the case second end such that the streamline flow conditioner is coupled radially between the case and the combustor liner such that the deflection plate is adjacent the case second end. The deflection plate inner surface at least one of extends radially outward with respect to the centerline and defines a plurality of openings within the plate inner surface.
摘要翻译：一种用于组装燃气轮机燃烧器的方法包括提供具有第一端，第二端和在其间延伸的中心线的燃烧器壳体，其将端盖连接到壳体的第一端部，将燃烧器衬套连接到壳体内，使得衬套相对于壳体基本上同轴对准，并且提供包括主体的流线型流动调节器，该主体包括径向外表面和径向内表面，偏转板从主体延伸，并将流线型流动调节器联接到壳体秒使得流线型流动调节器径向耦合在壳体和燃烧器衬套之间，使得偏转板与壳体的第二端相邻。偏转板内表面中的至少一个相对于中心线径向向外延伸并且在板内表面内限定多个开口。

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