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1. 发明授权

US6141967A Air fuel mixer for gas turbine combustor 失效
公开(公告)号：US6141967A
公开(公告)日：2000-11-07
申请号：US5343
申请日：1998-01-09
申请人： Paul R. Angel , James M. Caldwell , Narendra D. Joshi , Steven Marakovits , Kelley A. Foresman , Steven G. Goebel , Richard E. Warren, Jr.
发明人： Paul R. Angel , James M. Caldwell , Narendra D. Joshi , Steven Marakovits , Kelley A. Foresman , Steven G. Goebel , Richard E. Warren, Jr.
IPC分类号： F23R3/14 , F23R3/28 , F02C1/00
CPC分类号： F23R3/14 , F23R3/286
摘要： An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, including: a linear mixing duct having a circular cross-section defined by a wall; a centerbody located along a central axis of the mixing duct and extending substantially the full length of the mixing duct, the centerbody having a plurality of orifices therein to inject fuel into the mixing duct with an axial velocity component; a fuel supply in flow communication with the centerbody orifices; an outer annular swirler located adjacent an upstream end of the mixing duct and including a plurality of circumferentially spaced vanes oriented so as to swirl air flowing therethrough in a first direction; an inner annular swirler located adjacent the mixing duct upstream end and including a plurality of circumferentially spaced vanes, the vanes having an outer radial portion having a leading edge and a trailing edge oriented so as to swirl air flowing therethrough in a second direction opposite the first swirl direction by the outer annular swirler vanes and an inner radial portion with a leading edge and a trailing edge oriented so as to provide a boundary layer of air substantially along the centerbody; and, a hub separating the inner and outer annular swirlers to permit independent rotation of an air stream therethrough. The outer annular swirler may also include vanes having an inner radial portion with a leading edge and a trailing edge oriented so as to swirl the air flow therethrough and an outer radial portion having a leading edge and a trailing edge oriented so as to provide a boundary layer of air substantially along the mixing duct wall. High pressure air is injected from a compressor into the mixing duct through the inner and outer annular swirlers and fuel is injected into the mixing duct so that the high pressure air and the fuel is 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 a combustor and ignited.

2. 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。

3. 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.

4. 发明授权

US5675971A 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：US5675971A
公开(公告)日：1997-10-14
申请号：US581813
申请日：1996-01-02
申请人： Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean , Narendra D. Joshi
发明人： Paul R. Angel , James M. Caldwell , Paul V. Heberling , Anthony J. Dean , Narendra D. Joshi
IPC分类号： F23R3/28 , F02C1/00 , F02G3/00
CPC分类号： F23R3/286 , F23D2900/14004
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.
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，产生最小的污染物形成。

5. 发明授权

US06460340B1 Fuel nozzle for gas turbine engine and method of assembling 有权
标题翻译：燃气轮机用燃油喷嘴及组装方法
公开(公告)号：US06460340B1
公开(公告)日：2002-10-08
申请号：US09466557
申请日：1999-12-17
申请人： Claude H. Chauvette , Narendra D. Joshi
发明人： Claude H. Chauvette , Narendra D. Joshi
IPC分类号： F02C100
CPC分类号： F23R3/283 , B05B15/65 , F23D11/38 , F23D14/48 , Y10T29/49348
摘要： A fuel nozzle for a gas turbine engine has a spray tip and a housing coaxially disposed around the spray tip. Bi-directional axial movement of the spray tip relative to the housing is constrained by first and second rows of tabs formed on one of the housing and the spray tip and a third row of tabs formed on the other one of the housing and the spray tip. The third row of tabs is disposed between the first and second rows to constrain spray tip motion in either axial direction.
摘要翻译：用于燃气涡轮发动机的燃料喷嘴具有喷射尖端和围绕喷嘴同轴设置的壳体。喷嘴相对于壳体的双向轴向运动由形成在壳体和喷嘴顶端之一上的第一和第二排突片所限制，第三排突片形成在壳体和喷嘴的另一个上。第三排突片设置在第一和第二行之间以限制沿任一轴向的喷嘴端运动。

6. 发明授权

US6050082A Intercooled gas turbine engine with integral air bottoming cycle 失效
标题翻译：具有整体气底循环的中间燃气涡轮发动机
公开(公告)号：US6050082A
公开(公告)日：2000-04-18
申请号：US9192
申请日：1998-01-20
申请人： Gary L. Leonard , Narendra D. Joshi
发明人： Gary L. Leonard , Narendra D. Joshi
IPC分类号： F02C3/10 , F02C6/00 , F02C7/143 , F02C3/04 , F02C6/18
CPC分类号： F02C6/003 , F02C3/10 , F02C7/143 , Y02T50/675
摘要： A gas turbine engine that includes a 2/3 stage intercooled booster compressor is described. In one embodiment, the engine includes a low pressure turbine and a booster compressor rotatable on a low pressure shaft. The engine further includes a high pressure compressor, a high pressure combustor, and a high pressure turbine rotatable on a high pressure (HP) shaft and forming the core engine. A low pressure combustor is located at the outlet of the high pressure turbine and a power turbine. The booster compressor includes first and second stage compressors, and air flow from the first stage compressor is supplied to a first intercooler, and air flow from the second stage compressor is supplied to a second intercooler. Airflow from the first intercooler is supplied to the inlet of the second stage compressor, and airflow from the second intercooler is split between being provided to the inlet of the high pressure compressor and a recuperator. The recuperator also is coupled to receive air from the power turbine so that air from the power turbine heats air split away from the second stage compressor before being exhausted to atmosphere. Air heated in the recuperator drives the low pressure turbine connected to the booster compressors.
摘要翻译：描述了包括+ E，fra 2/3 + EE级中间冷却式增压压缩机的燃气涡轮发动机。在一个实施例中，发动机包括可在低压轴上旋转的低压涡轮机和增压压缩机。发动机还包括高压压缩机，高压燃烧器和可在高压（HP）轴上旋转并形成核心发动机的高压涡轮机。低压燃烧器位于高压涡轮机的出口处和动力涡轮机。增压压缩机包括第一级和第二级压缩机，并且来自第一级压缩机的空气流被供应到第一中间冷却器，并且来自第二级压缩机的空气流被供应到第二中间冷却器。来自第一中间冷却器的气流被供应到第二级压缩机的入口，并且来自第二中间冷却器的气流在被提供到高压压缩机的入口和换热器之间被分开。换热器还联接以从动力涡轮机接收空气，使得来自动力涡轮机的空气在排放到大气之前加热从第二级压缩机分离的空气。在换热器中加热的空气驱动连接到增压压缩机的低压涡轮机。

7. 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。

8. 发明授权

US5613363A Air fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的空气燃料混合器
公开(公告)号：US5613363A
公开(公告)日：1997-03-25
申请号：US312374
申请日：1994-09-26
申请人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
发明人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
IPC分类号： F23C7/00 , F23D11/10 , F23R3/14 , F23R3/28 , F02C3/20
CPC分类号： F23C7/004 , F23D11/107 , F23R3/14 , F23R3/286 , Y02T50/675
摘要： An air fuel mixer having a mixing duct, a set of inner and outer counter-rotating swirlers at the upstream end of the mixing duct, and means for injecting fuel into the mixing duct is provided, wherein 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 fuel nozzle by means of a plurality of fuel spokes so that 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 said mixing duct into the combustor and ignited.
摘要翻译：一种空气燃料混合器，其具有混合管道，一组在混合管道的上游端的内部和外部反向旋转旋流器，以及用于将燃料喷射到混合管道中的装置，其中将来自压缩机的高压空气注入通过旋流器形成强烈剪切区域的混合管道和燃料通过多个燃料辐条从燃料喷嘴喷射到混合管道中，使得高压空气和燃料均匀地混合在一起，从而产生最小的当燃料/空气混合物从所述混合管道的下游端排出到燃烧器中并点燃时，形成污染物。

9. 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。

10. 发明授权

US5590529A Air fuel mixer for gas turbine combustor 失效
标题翻译：燃气轮机燃烧器用空气燃料混合器
公开(公告)号：US5590529A
公开(公告)日：1997-01-07
申请号：US312373
申请日：1994-09-26
申请人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
发明人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
IPC分类号： F23D14/02 , F23R3/14 , F23R3/38 , F02C1/00
CPC分类号： F23R3/14 , F23D14/02 , F23R3/38 , Y02T50/675
摘要： An air fuel mixer having a mixing duct, a set of inner and outer counter-rotating swirlers at the upstream end of the mixing duct, and means for injecting fuel into the mixing duct is provided, wherein 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 fuel nozzle by means of a plurality of non-linear fuel spokes so that 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 said mixing duct into the combustor and ignited.
摘要翻译：一种空气燃料混合器，其具有混合管道，一组在混合管道的上游端的内部和外部反向旋转旋流器，以及用于将燃料喷射到混合管道中的装置，其中将来自压缩机的高压空气注入通过旋流器形成强烈剪切区域的混合管道和燃料通过多个非线性燃料辐条从燃料喷嘴喷射到混合管道中，使得高压空气和燃料均匀地混合在一起，以便当燃料/空气混合物从所述混合管道的下游端排出到燃烧器中并点燃时，产生最小的污染物形成。

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