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11. 发明授权

US4912931A Staged low NO.sub.x gas turbine combustor 失效
标题翻译：分级低NOx汽轮机燃烧器
公开(公告)号：US4912931A
公开(公告)日：1990-04-03
申请号：US109118
申请日：1987-10-16
申请人： Narendra D. Joshi , Frederick E. Moreno , Creighton D. Hartman
发明人： Narendra D. Joshi , Frederick E. Moreno , Creighton D. Hartman
IPC分类号： F23C6/04 , F23M5/00 , F23M5/08 , F23R3/00
CPC分类号： F23M5/00 , F23C6/045 , F23M5/085 , F23R3/002
摘要： A staged low NO.sub.x gas turbine combustor includes a refractory fibrous thermally insulatively lined primary combustion chamber, operating fuel-rich, and exhausting through a throat into a metallic secondary combustion chamber containing a fuel-lean secondary combustion zone in which combustion is completed. A radiation cooling zone is provided intermediate the throat and secondary combustion zone for cooling of the primary combustion products before quick quench in the secondary combustion zone. The fibrous lining of the primary combustion chamber is densified at its interior surface with a refractory such as zirconia or silicon carbide to inhibit flame erosion. The liner is wrapped with a supportive compliant blanket of fibrous refractory insulation. Air cooling of the metallic wall of the secondary chamber surrounding the radiation cooling zone is intensified relative to the remainder of the secondary combustion chamber.
摘要翻译：分级低NOx燃气轮机燃烧器包括耐火纤维热绝缘衬里的初级燃烧室，其操作富燃料，并通过喉部排入含有燃烧完成的燃料贫燃二次燃烧区的金属二次燃烧室。在二次燃烧区域中快速淬火之前，在喉部和二次燃烧区域之间设置辐射冷却区域，以冷却一次燃烧产物。主燃烧室的纤维衬里在其内表面上用耐火材料如氧化锆或碳化硅致密，以抑制火焰侵蚀。衬里用纤维耐火绝缘材料的支撑柔顺毯包裹。围绕辐射冷却区的次级室的金属壁的空气冷却相对于二级燃烧室的其余部分增强。

12. 发明授权

US5596873A Gas turbine combustor with a plurality of circumferentially spaced pre-mixers 失效
标题翻译：具有多个周向间隔的预混合器的燃气轮机燃烧器
公开(公告)号：US5596873A
公开(公告)日：1997-01-28
申请号：US305629
申请日：1994-09-14
申请人： Narendra D. Joshi , John M. Koshoffer
发明人： Narendra D. Joshi , John M. Koshoffer
IPC分类号： F23R3/28 , F23R3/50 , F02C7/08
CPC分类号： F23R3/50 , F23R3/286 , F05B2240/40
摘要： An annular combustor with an air fuel mixer is disclosed including a plurality of mixing tubes having a forward end and an exit end, wherein a longitudinal axis through the exit end for each mixing tube is at both an axial angle and a radial angle to the centerline axis of the mixer. A fuel injector for providing fuel to the forward end of each mixing tube, a fuel manifold in flow communication with each of the fuel injectors, and a fuel supply and control means are provided. High pressure air from a compressor is injected into the mixing tubes and fuel is injected into the mixing tubes from the fuel injectors, wherein the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of the mixing tubes into the combustor and combusted. The mixing tubes preferably impart a swirl to the fuel/air mixture as it exits into the combustor.
摘要翻译：公开了一种具有空气燃料混合器的环形燃烧器，其包括具有前端和出口端的多个混合管，其中通过每个混合管的出口端的纵向轴线与中心线处于轴向角度和径向角度搅拌机轴。提供一种用于向每个混合管的前端提供燃料的燃料喷射器，与每个燃料喷射器流动连通的燃料歧管以及燃料供应和控制装置。来自压缩机的高压空气被注入到混合管中，并且燃料从燃料喷射器注入到混合管中，其中高压空气和燃料均匀混合在其中，以便当燃料/空气混合物从混合管的下游端排出到燃烧器中并燃烧。混合管优选在燃料/空气混合物离开燃烧器时给予涡流。

13. 发明授权

US4910957A Staged lean premix low nox hot wall gas turbine combustor with improved turndown capability 失效
标题翻译：分级精益预混低低温壁式燃气轮机燃烧器具有改进的调节能力
公开(公告)号：US4910957A
公开(公告)日：1990-03-27
申请号：US218253
申请日：1988-07-13
申请人： Frederick E. Moreno , Narendra D. Joshi
发明人： Frederick E. Moreno , Narendra D. Joshi
IPC分类号： F02C3/14 , F23R3/00 , F23R3/34
CPC分类号： F23R3/346 , F02C3/14 , F23R3/007 , F05D2270/31
摘要： In a staged lean premix low NOx gas turbine combustor, the inside of the combustor is lined with a low density refractory thermal insulator for maintaining the hot face of the lining at or near the flame temperature, i.e., within 200.degree. F. and preferably within 50.degree. F. The heat release value in the first stage is held at a maximum value consistent with low NOx emission while decreasing the heat release value in the second or third stage to achieve a wide range of turndown. The flame temperature in the respective stages are maintained between a low of 1700.degree. F. and a maximum of 2700.degree. F. The flow of compressed air into the combustor is maintained generally uniform over the entire operating range of 5 to 1 turndown.
摘要翻译：在分阶段的精简预混合低NOx燃气轮机燃烧器中，燃烧器内部衬有低密度耐火绝热材料，用于将衬里的热面保持在火焰温度处或接近火焰温度，即在200°F以内，优选在 50°F。第一级中的放热值保持在与低NOx排放一致的最大值，同时降低第二级或第三级的放热值，以实现宽范围的调节。各阶段的火焰温度保持在1700°F的最低值和2700°F之间。压缩空气进入燃烧器的流动在5至1个调节范围的整个工作范围内保持一般均匀。

14. 发明授权

US4928481A Staged low NOx premix gas turbine combustor 失效
标题翻译：分期低NOx预混燃气轮机燃烧器
公开(公告)号：US4928481A
公开(公告)日：1990-05-29
申请号：US218252
申请日：1988-07-13
申请人： Narendra D. Joshi , Frederick E. Moreno
发明人： Narendra D. Joshi , Frederick E. Moreno
IPC分类号： F23R3/34
CPC分类号： F23R3/346
摘要： In a staged low NOx lean premix hot wall gas turbine combustor, the interior wall of the combustor is maintained at or near the flame temperature to provide stable operation over a wide range of heat release values. One or more stages of the staged combustor includes a Stirred Reactor region followed by a Plug Flow Reactor region. In one embodiment, a lean premixture of fuel and air is inducted tangentially into an annular intake manifold for inducting a cyclonic flow of the premixture into the combustion chamber. In another embodiment, the Stirred Reactor region is developed by colliding, preferably head-on, a plurality of jets of lean premixture within the combustion chamber.
摘要翻译：在分级的低NOx稀燃预混热壁燃气涡轮机燃烧器中，燃烧器的内壁保持在或接近火焰温度以在宽范围的散热值上提供稳定的操作。分级燃烧器的一个或多个阶段包括搅拌反应器区域，随后是塞流反应器区域。在一个实施例中，燃料和空气的贫预混合物被切向地引入环形进气歧管中，用于将预混合物的气旋流引入燃烧室。在另一个实施方案中，搅拌反应器区域是通过在燃烧室内碰撞，优选地在多个喷射的稀薄预混合物上而开发的。

15. 发明授权

US06449953B1 Methods for reducing gas turbine engine emissions 有权
标题翻译：减少燃气轮机发动机排放的方法
公开(公告)号：US06449953B1
公开(公告)日：2002-09-17
申请号：US09560459
申请日：2000-04-28
申请人： Richard B. Hook, Jr. , M. Waseem Adhami , Narendra D. Joshi
发明人： Richard B. Hook, Jr. , M. Waseem Adhami , Narendra D. Joshi
IPC分类号： F02C330
CPC分类号： F02C3/30 , F05D2220/32
摘要： A gas turbine engine includes a compressor rotor assembly including a first rotor, a combustor configured to operate with a fuel/air mixture equivalence ratio less than one, and a water injection assembly. The water injection assembly includes a water delivery system including a first plurality of spray nozzles to supply water upstream from the first rotor. The water being supplied to the first rotor is atomized with the first plurality of spray nozzles prior to being supplied to the engine to lower the emissions generated by the combustor.
摘要翻译：燃气涡轮发动机包括压缩机转子组件，该压缩机转子组件包括第一转子，构造成以小于1的燃料/空气混合物当量比操作的燃烧器和水喷射组件。注水组件包括水输送系统，其包括第一多个喷嘴，以从第一转子上游供水。供给到第一转子的水在被供给到发动机之前用第一多个喷嘴雾化，以降低由燃烧器产生的排放。

16. 发明授权

US5778676A Dual fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的双燃料混合器
公开(公告)号：US5778676A
公开(公告)日：1998-07-14
申请号：US581817
申请日：1996-01-02
申请人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
发明人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
IPC分类号： F23D11/10 , F23D17/00 , F23R3/14 , F23R3/36 , F02C1/00 , F02G3/00
CPC分类号： F23R3/14 , F23D11/101 , F23D17/002 , F23R3/36 , F23C2900/07001 , F23D2209/10 , F23D2209/30
摘要： An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities. A second fuel can be injected into the mixing duct by means of a plurality of orifices in the centerbody wall which are in flow communication with a fuel supply and control means. In this way, high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the outer swirler vane passages and/or the centerbody orifices so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of poullutants when a fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.
摘要翻译：公开了一种空气燃料混合器，其具有混合管道，围绕混合管道的上游端的护罩，其中设置有与燃料供应和控制装置流动连通的燃料歧管，一组相邻的内部和外部反向旋转旋流器混合管道的上游端，用于向气流产生涡流;轮毂，分隔内外环形旋流器，以允许空气流的独立旋转;以及沿着混合管道的大致整个长度方向定位的中心体。为了将一种类型的燃料喷射到混合管道中，燃料被供应到外部环形旋流器，其包括具有内部空腔的中空叶片，其中外部旋流器叶片的内部空腔与护罩中的燃料歧管流体连通。外旋流器叶片还包括与内腔流动连通的多个通过其的燃料通道。第二燃料可以通过与燃料供应和控制装置流动连通的中心体壁中的多个喷嘴喷射到混合管道中。以这种方式，来自压缩机的高压空气通过旋流器喷射到混合管道中以形成强烈的剪切区域，并且燃料从外部旋流器叶片通道和/或中心体孔口喷射到混合管道中，使得高压空气和燃料均匀地混合在一起，以便当燃料/空气混合物从混合管道的下游端排出到燃烧器中并点燃时，产生最小的起泡器的形成。

17. 发明授权

US06536206B2 Apparatus for decreasing combustor emissions 有权
标题翻译：减少燃烧器排放的装置
公开(公告)号：US06536206B2
公开(公告)日：2003-03-25
申请号：US10176875
申请日：2002-06-21
申请人： Richard B. Hook, Jr. , M. Waseem Adhami , Narendra D. Joshi
发明人： Richard B. Hook, Jr. , M. Waseem Adhami , Narendra D. Joshi
IPC分类号： F02C330
CPC分类号： F02C3/30 , F05D2220/32
摘要： A gas turbine engine includes a compressor rotor assembly including a first rotor, a combustor configured to operate with a fuel/air mixture equivalence ratio less than one, and a water injection assembly. The water injection assembly includes a water delivery system including a first plurality of spray nozzles to supply water upstream from the first rotor. The water being supplied to the first rotor is atomized with the first plurality of spray nozzles prior to being supplied to the engine to lower the emissions generated by the combustor.
摘要翻译：燃气涡轮发动机包括压缩机转子组件，该压缩机转子组件包括第一转子，构造成以小于1的燃料/空气混合物当量比操作的燃烧器和水喷射组件。注水组件包括水输送系统，其包括第一多个喷嘴，以从第一转子上游供水。供给到第一转子的水在被供给到发动机之前用第一多个喷嘴雾化，以降低由燃烧器产生的排放。

18. 发明授权

US5865024A Dual fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的双燃料混合器
公开(公告)号：US5865024A
公开(公告)日：1999-02-02
申请号：US783521
申请日：1997-01-14
申请人： Eric J. Kress , Narendra D. Joshi
发明人： Eric J. Kress , Narendra D. Joshi
IPC分类号： F23D14/62 , F23D17/00 , F23R3/14 , F23R3/28 , F23R3/36 , F23R3/32
CPC分类号： F23D17/002 , F23D14/62 , F23R3/14 , F23R3/286 , F23R3/36 , F23D2206/10
摘要： A dual fuel mixer is disclosed as including a mixing duct having an upstream end, a downstream end, and a centerline axis therethrough, where the mixing duct has a circular cross-section defined by a wall. A shroud surrounds the upstream end of the mixing duct and contains therein a gas manifold in flow communication with a gas fuel supply and control. A set of inner and outer annular counter-rotating swirlers are located adjacent the upstream end of the mixing duct for imparting swirl to an air stream. The outer annular swirler includes hollow vanes with internal cavities which are in flow communication with the gas manifold, the outer swirler vanes also having a plurality of gas fuel passages therethrough in flow communication with the internal cavities to inject gas fuel into the air stream. A hub is provided for separating the inner and outer annular swirlers to allow independent rotation thereof. A fuel injector is substantially aligned with the centerline axis for injecting liquid fuel axially into the upstream end of the mixing duct. High pressure air from a compressor is injected into the mixing duct through the inner and outer swirlers to form an intense shear region so that gas fuel injected into the mixing duct from the outer swirler vane passages and/or liquid fuel injected into the mixing duct from the fuel injector are uniformly mixed therein, whereby minimal formation of pollutants is produced when the fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.
摘要翻译：公开了一种双燃料混合器，其包括具有上游端，下游端和穿过其中心线的混合管道，其中混合管道具有由壁限定的圆形横截面。护罩围绕混合管道的上游端并且容纳有与气体燃料供应和控制流动连通的气体歧管。一组内外环形反向旋转旋流器位于混合管道的上游端附近，用于向气流施加漩涡。外部环形旋流器包括具有与气体歧管流动连通的内部空腔的中空叶片，外部旋流器叶片还具有与内部空腔流体连通的多个气体燃料通道，以将气体燃料喷射到空气流中。提供用于分离内环形旋流器和外环形旋流器以允许其独立旋转的毂。燃料喷射器基本上与中心线轴线对准，用于将液体燃料轴向注入混合管道的上游端。来自压缩机的高压空气通过内旋流器和外旋流器喷射到混合管道中，以形成强烈的剪切区域，使得从外旋流器叶片通道和/或喷射到混合管道中的液体燃料喷射到混合管道中的气体燃料燃料喷射器被均匀地混合在一起，当燃料/空气混合物从混合管道的下游端排出到燃烧器中并被点燃时，产生最小的污染物形成。

19. 发明授权

US5816049A Dual fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的双燃料混合器
公开(公告)号：US5816049A
公开(公告)日：1998-10-06
申请号：US778133
申请日：1997-01-02
申请人： Narendra D. Joshi
发明人： Narendra D. Joshi
IPC分类号： F23C7/00 , F23D17/00 , F23R3/14 , F23R3/36
CPC分类号： F23C7/004 , F23D17/002 , F23R3/14 , F23C2900/07001 , F23D2206/10 , F23D2900/14021
摘要： An apparatus for premixing fuel and air prior to combustion in a gas turbine engine is disclosed as including a linear mixing duct having a circular cross-section defined by a wall. A gas fuel manifold is positioned adjacent the upstream end of the mixing duct and is in flow communication with a gas fuel supply and control means. An outer annular swirler is oriented radially to the mixing duct and positioned adjacent the upstream end of the mixing duct to impart swirl to an air stream entering the outer annular swirler. The outer annular swirler includes hollow vanes with internal cavities which are in flow communication with the gas manifold, the outer swirler vanes also having a plurality of gas fuel passages therethrough in flow communication with the internal cavities to inject gas fuel into the radially-oriented air stream. An inner annular swirler is oriented axially with the mixing duct and positioned adjacent the upstream end of the mixing duct to impart swirl to an air stream entering the inner annular swirler. A holder is provided for connecting the inner and outer annular swirlers in radially spaced relation so that a passage is formed upstream of the mixing duct to direct the radially-oriented air stream swirled by the outer annular swirler into the mixing duct. The holder includes an internal cavity therein with a plurality of passages in flow communication therewith which terminate as openings along an outer radial surface of the holder. A liquid fuel manifold is positioned within the holder internal cavity and is in flow communication with a liquid fuel supply and control means. The liquid fuel manifold is also in flow communication with a fuel tube positioned in each of the holder passages to inject liquid fuel into the radially-oriented air stream directed into the mixing duct.
摘要翻译：公开了一种用于在燃气涡轮发动机中燃烧之前预混合燃料和空气的装置，包括具有由壁限定的圆形横截面的线性混合管道。气体燃料歧管位于混合管道的上游端附近并与气体燃料供应和控制装置流动连通。外部环形旋流器径向地定向到混合管道并且位于混合管道的上游端附近，以对进入外部环形旋流器的空气流赋予涡流。外部环形旋流器包括具有与气体歧管流动连通的内部空腔的中空叶片，外部旋流器叶片还具有与内部空腔流体连通的多个气体燃料通道，以将气体燃料喷射到径向取向的空气中流。内环形旋流器与混合管道轴向定向并且邻近混合管道的上游端定位，以使进入内环形旋流器的空气流产生涡流。设置有用于以径向间隔的关系连接内环形旋流器和外环形旋流器的保持器，使得在混合管道的上游形成通道，以将由外环形旋流器旋转的径向取向的空气流引导到混合管道中。保持器包括内部空腔，其中具有与其连通的多个通道，其以作为保持器的外径向表面的开口终止。液体燃料歧管位于保持器内部空腔内并且与液体燃料供应和控制装置流动连通。液体燃料歧管还与位于每个保持器通道中的燃料管流动连通，以将液体燃料注入到引导到混合管道中的径向取向的空气流中。

20. 发明授权

US5680766A Dual fuel mixer for gas turbine combustor 失效
公开(公告)号：US5680766A
公开(公告)日：1997-10-28
申请号：US581818
申请日：1996-01-02
申请人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
发明人： Narendra D. Joshi , Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean
IPC分类号： F23C7/00 , F23D17/00 , F23R3/14 , F23R3/36 , F02C1/00
CPC分类号： F23R3/36 , F23C7/004 , F23D17/002 , F23R3/14 , F23C2900/07001 , F23D2209/30
摘要： An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities. A second fuel can be injected into the mixing duct by means of a plurality of orifices in the centerbody wall which are in flow communication with a fuel supply and control means. In this way, high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the outer swirler vane passages and/or the centerbody orifices so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when a fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.

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