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1. 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。

2. 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.

3. 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。

4. 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。

5. 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。

6. 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。

7. 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。

8. 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。

9. 发明授权

US5251447A 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：US5251447A
公开(公告)日：1993-10-12
申请号：US955379
申请日：1992-10-01
申请人： Narendra D. Joshi , Edward E. Ekstedt , Michael J. Epstein
发明人： Narendra D. Joshi , Edward E. Ekstedt , Michael J. Epstein
IPC分类号： F23R3/14 , F23R3/32
CPC分类号： F23R3/14 , F05B2250/411
摘要： An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct having contained therein a fuel manifold 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, hollow vanes in at least the outer swirler having passages therethrough in fluid communication with the fuel manifold to inject fuel into the mixing duct, and a hub separating the inner and outer swirlers to allow independent rotation thereof, 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 swirler vanes 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 the mixing duct into the combustor and ignited. Further, the air fuel mixer of the present invention may include passages in the wall of the mixing duct in fluid communication with the fuel manifold, a centerbody in the mixing duct having a passage therethrough to admit air into the downstream end of the mixing duct, and tubes extending from the passages in the swirler vanes and/or mixing duct wall to inject liquid fuel downstream of the swirlers.
摘要翻译：公开了一种具有混合管道的空气燃料混合器，围绕混合管道的上游端的护罩，其中容纳有与燃料供应和控制装置流体连通的燃料歧管，与燃料供应和控制装置相邻的一组内部和外部反向旋转旋流器至少外旋流器的中空叶片具有与燃料歧管流体连通的通道，以将燃料喷射到混合管道中;以及毂，分离内旋流器和外旋流器以允许其独立旋转，其中高来自压缩机的压力空气通过旋流器注入混合管道中以形成强烈的剪切区域，并且燃料从旋流器叶片注入到混合管道中，使得高压空气和燃料均匀地混合在其中，从而产生最小的当燃料/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，形成污染物。此外，本发明的空气燃料混合器可以包括在与燃料歧管流体连通的混合管道的壁中的通道，混合管道中的中心体具有穿过其中的通道，以将空气吸入混合管道的下游端，以及从旋流器叶片和/或混合管道壁中的通道延伸的管以在旋流器下游注入液体燃料。

10. 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。

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