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1. 发明授权

US08701383B2 Late lean injection system configuration 有权
标题翻译：后倾注射系统配置
公开(公告)号：US08701383B2
公开(公告)日：2014-04-22
申请号：US12349831
申请日：2009-01-07
申请人： Krishna Kumar Venkataraman , Roy Marshall Washam , Hasan Karim , Jason Charles Terry , Lewis Berkley Davis, Jr.
发明人： Krishna Kumar Venkataraman , Roy Marshall Washam , Hasan Karim , Jason Charles Terry , Lewis Berkley Davis, Jr.
IPC分类号： F02C7/228 , F23R3/34 , F23R3/36
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
摘要翻译：提供了一种燃气涡轮发动机，并且包括具有第一内部的后倾稀注射（LLI）兼容的燃烧器，其中由燃料回路供应到其中的第一燃料可燃，涡轮机，过渡区域，其中第二内部由燃料回路供应的燃料和第一燃料的燃烧产物是可燃的，过渡区设置成使燃烧器和涡轮彼此流体连接，并且多个燃料喷射器在结构上由过渡区并且连接到燃料回路，并且其构造成在单个轴向级，多个轴向级，单个轴向圆周级和多个轴向圆周级中的任一个中将第二燃料供应到第二内部。

2. 发明申请

US20120308947A1 COMBUSTOR HAVING A PRESSURE FEED 审中-公开
标题翻译：具有压力进给的燃烧器
公开(公告)号：US20120308947A1
公开(公告)日：2012-12-06
申请号：US13154027
申请日：2011-06-06
申请人： Patrick Benedict Melton , David Leach , Robert Joseph Rohrssen , Roy Marshall Washam
发明人： Patrick Benedict Melton , David Leach , Robert Joseph Rohrssen , Roy Marshall Washam
IPC分类号： F23C7/00 , B21D53/00
CPC分类号： F23R3/002 , F23R3/04 , F23R3/10 , F23R3/286 , F23R2900/03044 , Y10T29/49348
摘要： A combustor having a pressure feed is provided and includes an outer vessel, an intermediate vessel disposed within the outer vessel to form an outer annulus, an inner vessel disposed within the intermediate vessel to form an inner annulus between the intermediate and inner vessels, by which upstream portions of fuel nozzles disposed within the inner vessel are fed, and an internal volume within the inner vessel about downstream portions of the fuel nozzles and a tubular assembly by which the outer annulus and the internal volume are communicative.
摘要翻译：提供了具有压力进料的燃烧器，并且包括外部容器，设置在外部容器内以形成外部环空的中间容器，设置在中间容器内的内部容器，以在中间容器和内部容器之间形成内部环空，供给设置在内部容器内的燃料喷嘴的上游部分，以及内部容器内的内部容积，其内部容器围绕燃料喷嘴的下游部分和管状组件，外部环空和内部容积通过该管状组件连通。

3. 发明申请

US20120036863A1 METHOD, APPARATUS AND SYSTEM FOR DELIVERY OF WIDE RANGE OF TURBINE FUELS FOR COMBUSTION 审中-公开
标题翻译：用于输送涡轮燃料燃料的宽范围的方法，装置和系统
公开(公告)号：US20120036863A1
公开(公告)日：2012-02-16
申请号：US12856107
申请日：2010-08-13
申请人： Joseph Kirzhner , Predrag Popovic , Roy Marshall Washam
发明人： Joseph Kirzhner , Predrag Popovic , Roy Marshall Washam
IPC分类号： F02C7/22 , F02C9/00
CPC分类号： F02C7/22 , F02C9/34 , F02C9/40
摘要： In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for sustainable combustion during various stages of the turbine operation. In one aspect, combustible lean limit operation of the gas turbine free of lean blow out is enabled by adjusting fuel-air-ratio of the fuel and fuel-air mixture properties, based on the operation requirements of the turbine and flammability of the fuel components.
摘要翻译：在操作燃气轮机时，在涡轮机运行的各个阶段期间燃料的期望的热值与用于可持续燃烧的燃料的实际需要之间可能存在差异。在一个方面，通过基于涡轮机的操作要求和燃料组分的可燃性调节燃料和燃料 - 空气混合物性质的燃料空气比，能够实现无烟气的燃气轮机的可燃稀薄限制操作。

4. 发明申请

US20110225947A1 SYSTEM AND METHODS FOR ALTERING AIR FLOW IN A COMBUSTOR 审中-公开
标题翻译：用于改变燃烧器中的空气流的系统和方法
公开(公告)号：US20110225947A1
公开(公告)日：2011-09-22
申请号：US12725602
申请日：2010-03-17
申请人： Benjamin Paul Lacy , Roy Marshall Washam , Thomas Edward Johnson
发明人： Benjamin Paul Lacy , Roy Marshall Washam , Thomas Edward Johnson
IPC分类号： F23R3/26 , F02C3/14 , F02C7/22
CPC分类号： F23R3/26 , F23R3/286
摘要： A combustor assembly of a turbine engine is provided with a mechanical air regulation unit which selectively varies the amount of air being delivered into a combustion zone of the combustor based upon a pressure of a fuel being supplied to the combustor. A first type of air regulation unit would act to increase the amount of air entering the combustion zone when greater amounts of a high heat value fuel are being delivered to the fuel nozzles of the combustor. A second type of air regulation unit could act to decrease the amount of air entering the combustion zone when greater amounts of a low heat value fuel are being delivered into the combustor through fuel nozzles.
摘要翻译：涡轮发动机的燃烧器组件设置有机械空气调节单元，其基于供应到燃烧器的燃料的压力选择性地改变被输送到燃烧器的燃烧区域中的空气量。当更大量的高热值燃料被输送到燃烧器的燃料喷嘴时，第一类型的空气调节单元将用于增加进入燃烧区域的空气量。当较大量的低热值燃料通过燃料喷嘴输送到燃烧器中时，第二类型的空气调节单元可以起到减少进入燃烧区域的空气量的作用。

5. 发明申请

US20130180253A1 SYSTEM AND METHOD FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR 审中-公开
标题翻译：向工作人员提供工作流体的系统和方法
公开(公告)号：US20130180253A1
公开(公告)日：2013-07-18
申请号：US13349886
申请日：2012-01-13
申请人： Lucas John Stoia , Patrick Benedict Melton , Roy Marshall Washam
发明人： Lucas John Stoia , Patrick Benedict Melton , Roy Marshall Washam
IPC分类号： F23R3/28
CPC分类号： F23R3/04 , F23R3/346
摘要： A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber, and fuel injectors circumferentially arranged around the combustion chamber. A combustor casing surrounds the combustion chamber. A distribution manifold encloses the fuel injectors, and a plenum passes through the combustor casing. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber, diverting a portion of the working fluid into a plenum, and flowing the diverted portion of the working fluid outside of the compressor and the combustor. The method further includes flowing the diverted portion of the working fluid through a combustor casing and through a distribution manifold that encloses fuel injectors circumferentially arranged around the combustion chamber.
摘要翻译：用于向燃烧器供应工作流体的系统包括燃料喷嘴，燃烧室和围绕燃烧室周向布置的燃料喷射器。燃烧器壳体围绕燃烧室。分配歧管围绕燃料喷射器，并且气室通过燃烧器壳体。将工作流体供给到燃烧器的方法包括使来自压缩机的工作流体流过燃烧室，将工作流体的一部分转移到集气室中，并使工作流体的转向部分流出压缩机和燃烧器外部。该方法还包括使工作流体的转向部分流过燃烧器壳体并且通过围绕燃烧室周向布置的围绕燃料喷射器的分配歧管流动。

6. 发明授权

US08215116B2 System and method for air-fuel mixing in gas turbines 失效
标题翻译：燃气轮机空气燃料混合的系统和方法
公开(公告)号：US08215116B2
公开(公告)日：2012-07-10
申请号：US12244696
申请日：2008-10-02
申请人： Luiz C. V. Fernandes , Elias Marquez , Roy Marshall Washam
发明人： Luiz C. V. Fernandes , Elias Marquez , Roy Marshall Washam
IPC分类号： F02C1/00
CPC分类号： F23R3/286
摘要： A system includes a fuel nozzle for a turbine engine that includes a tapered central body located at an interior base of the fuel nozzle, an air swirler, and a fuel port in the tapered central body, separate from the air swirler.
摘要翻译：一种系统包括用于涡轮发动机的燃料喷嘴，该燃料喷嘴包括位于燃料喷嘴的内部基座的锥形中心体，空气旋流器以及与空气旋流器分离的锥形中心体中的燃料口。

7. 发明申请

US20100170216A1 LATE LEAN INJECTION SYSTEM CONFIGURATION 有权
标题翻译：最佳注射系统配置
公开(公告)号：US20100170216A1
公开(公告)日：2010-07-08
申请号：US12349831
申请日：2009-01-07
申请人： Krishna Kumar Venkataraman , Roy Marshall Washam , Hasan Karim , Jason Charles Terry , Lewis Berkley Davis, JR.
发明人： Krishna Kumar Venkataraman , Roy Marshall Washam , Hasan Karim , Jason Charles Terry , Lewis Berkley Davis, JR.
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.
摘要翻译：提供了一种燃气涡轮发动机，并且包括具有第一内部的后倾稀注射（LLI）兼容的燃烧器，其中由燃料回路供应到其中的第一燃料可燃，涡轮机，过渡区域，其中第二内部由燃料回路供应的燃料和第一燃料的燃烧产物是可燃的，过渡区设置成使燃烧器和涡轮彼此流体连接，并且多个燃料喷射器在结构上由过渡区并且连接到燃料回路，并且其构造成在单个轴向级，多个轴向级，单个轴向圆周级和多个轴向圆周级中的任一个中将第二燃料供应到第二内部。

8. 发明授权

US08707672B2 Apparatus and method for cooling a combustor cap 有权
标题翻译：用于冷却燃烧器盖的装置和方法
公开(公告)号：US08707672B2
公开(公告)日：2014-04-29
申请号：US12879238
申请日：2010-09-10
申请人： Baifang Zuo , Roy Marshall Washam , Chunyang Wu
发明人： Baifang Zuo , Roy Marshall Washam , Chunyang Wu
IPC分类号： F02C3/00
CPC分类号： F01D25/12 , F05D2260/201 , F23R3/002 , F23R3/10 , F23R3/283 , F23R3/54 , F23R2900/03042 , F23R2900/03044
摘要： A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.
摘要翻译：燃烧器包括具有穿孔的下游板和在下游板下游的燃烧室的端盖。增压室与下游板流体连通，并通过下游板中的穿孔将冷却介质提供给燃烧室。一种用于冷却燃烧器的方法包括将冷却介质流入燃烧器端盖并将冷却介质撞击在燃烧器端盖中的下游板上。该方法还包括通过下游板中的穿孔使冷却介质流入燃烧室。

9. 发明申请

US20130067927A1 SYSTEM AND METHOD FOR CONTROLLING COMBUSTION INSTABILITIES IN GAS TURBINE SYSTEMS 审中-公开
标题翻译：用于控制气体涡轮机系统中燃烧不稳定性的系统和方法
公开(公告)号：US20130067927A1
公开(公告)日：2013-03-21
申请号：US13234493
申请日：2011-09-16
申请人： Joseph Kirzhner , Roy Marshall Washam
发明人： Joseph Kirzhner , Roy Marshall Washam
IPC分类号： F23R3/28 , F02C9/00 , F23R3/42
CPC分类号： F23R3/46 , F23C9/00 , F23L7/00 , F23N5/003 , F23N2021/12 , F23N2025/26 , F23N2037/02 , F23N2041/20 , F23R3/16 , F23R3/28 , F23R2900/00013
摘要： A gas turbine system and a method for controlling combustion instability in a combustion section of a gas turbine system are disclosed. The gas turbine system includes a compressor section, a turbine section connected to the compressor section, and a combustor section connected to the compressor section and the turbine section. The combustor section includes a plurality of combustors. The combustor section further includes at least one igniter for igniting a fuel-air mixture within each of the plurality of combustors into a hot gas. The gas turbine system further includes a control system for controlling a velocity of the hot gas in at least one of the plurality of combustors by controlling an operating parameter of the fuel-air mixture.
摘要翻译：公开了一种燃气轮机系统和用于控制燃气轮机系统的燃烧部分中的燃烧不稳定性的方法。燃气轮机系统包括压缩机部分，连接到压缩机部分的涡轮部分和连接到压缩机部分和涡轮部分的燃烧器部分。燃烧器部分包括多个燃烧器。燃烧器部分还包括至少一个点火器，用于将多个燃烧器中的每一个内的燃料 - 空气混合物点燃成热气体。燃气轮机系统还包括控制系统，用于通过控制燃料 - 空气混合物的操作参数来控制多个燃烧器中的至少一个中的热气体的速度。

10. 发明申请

US20120060511A1 APPARATUS AND METHOD FOR COOLING A COMBUSTOR CAP 有权
标题翻译：用于冷却燃烧器盖的装置和方法
公开(公告)号：US20120060511A1
公开(公告)日：2012-03-15
申请号：US12879238
申请日：2010-09-10
申请人： Baifang Zuo , Roy Marshall Washam , Chunyang Wu
发明人： Baifang Zuo , Roy Marshall Washam , Chunyang Wu
IPC分类号： F01D25/12 , F02C7/12
CPC分类号： F01D25/12 , F05D2260/201 , F23R3/002 , F23R3/10 , F23R3/283 , F23R3/54 , F23R2900/03042 , F23R2900/03044
摘要： A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.
摘要翻译：燃烧器包括具有穿孔的下游板和在下游板下游的燃烧室的端盖。增压室与下游板流体连通，并通过下游板中的穿孔将冷却介质提供给燃烧室。一种用于冷却燃烧器的方法包括将冷却介质流入燃烧器端盖并将冷却介质撞击在燃烧器端盖中的下游板上。该方法还包括通过下游板中的穿孔使冷却介质流入燃烧室。

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