专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08646276B2 Combustor assembly for a turbine engine with enhanced cooling 有权
标题翻译：用于具有增强冷却的涡轮发动机的燃烧器组件
公开(公告)号：US08646276B2
公开(公告)日：2014-02-11
申请号：US12616304
申请日：2009-11-11
申请人： Lewis Berkley Davis, Jr. , Ronald James Chila
发明人： Lewis Berkley Davis, Jr. , Ronald James Chila
IPC分类号： F02C1/00
CPC分类号： F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03043 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.
摘要翻译：用于涡轮发动机的燃烧器组件包括燃烧器衬套和围绕燃烧器衬套的流动套管。压缩空气流过位于燃烧器衬套的外表面和流动套管的内表面之间的环形空间。通过流动套筒形成多个冷却孔，以允许压缩空气从流动套筒外部的位置流过冷却孔并进入环形空间。环形空间的高度可以沿着燃烧器组件的长度而变化。因此，流动套管可以具有减小的直径部分，这导致环形空间的高度在某些位置比沿着燃烧器组件的长度的其它位置更小。

2. 发明授权

US09822649B2 Integrated combustor and stage 1 nozzle in a gas turbine and method 有权
公开(公告)号：US09822649B2
公开(公告)日：2017-11-21
申请号：US12269411
申请日：2008-11-12
申请人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
发明人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
IPC分类号： F01C1/00 , F01D9/02 , F01D9/04 , F23R3/00 , F23R3/28 , F23R3/46
CPC分类号： F01D9/023 , F01D9/041 , F23R3/002 , F23R3/286 , F23R3/46 , Y02T50/675
摘要： An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

3. 发明授权

US08695322B2 Thermally decoupled can-annular transition piece 有权
标题翻译：热分离的罐环过渡件
公开(公告)号：US08695322B2
公开(公告)日：2014-04-15
申请号：US12413991
申请日：2009-03-30
申请人： Lewis Berkley Davis, Jr. , Ronald James Chila
发明人： Lewis Berkley Davis, Jr. , Ronald James Chila
IPC分类号： F01D9/02 , F23R3/06
CPC分类号： F01D9/023 , F05D2230/642 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/31 , F05D2260/36
摘要： A turbomachine includes a plurality of injection nozzles arranged in a can-annular array and a transition piece including at least one wall that defines a combustion flow passage. A dilution orifice is formed in the at least one wall of the transition piece. The dilution orifice guides dilution gases to the combustion flow passage. A heat shield member is mounted to the at least one wall of the transition piece in the combustion flow passage. The heat shield member includes a body having a first surface and an opposing second surface through which extends a dilution passage. The dilution passage is off-set from the dilution orifice. The heat shield member is spaced from the at least one wall of the transition piece defining a flow region between the at least one wall and the second surface.
摘要翻译：涡轮机包括以罐形环形阵列布置的多个注射喷嘴和包括限定燃烧流动通道的至少一个壁的过渡件。在过渡件的至少一个壁上形成有稀释孔。稀释孔将稀释气体引导到燃烧流动通道。在燃烧流路中的过渡件的至少一个壁上安装有隔热构件。隔热构件包括具有第一表面和相对的第二表面的主体，通过该主体延伸稀释通道。稀释通道从稀释孔偏离。隔热构件与过渡件的至少一个壁间隔开，限定了至少一个壁和第二表面之间的流动区域。

4. 发明授权

US08448416B2 Combustor liner 有权
标题翻译：燃烧器衬管
公开(公告)号：US08448416B2
公开(公告)日：2013-05-28
申请号：US12414003
申请日：2009-03-30
申请人： Lewis Berkley Davis, Jr. , Ronald James Chila
发明人： Lewis Berkley Davis, Jr. , Ronald James Chila
IPC分类号： F23R3/26 , F02C1/00 , F23R3/00
CPC分类号： F23R3/26 , F23M2900/05004 , F23R3/002 , F23R3/02 , F23R3/06 , F23R3/60 , F23R2900/03045 , Y02T50/67 , Y02T50/675
摘要： A combustor within which a combustion zone is defined is provided and includes an annular liner having a first mixing hole defined therein at a first axial position, a flow sleeve, having a second mixing hole defined therein at a second axial position, the flow sleeve surrounding the liner to form a first flow space at an exterior of the liner, a port, coupled to the flow sleeve at the second axial position, which is configured to remove air from the first flow space via the second mixing hole, and a shield, having a third mixing hole defined therein at the second axial position, the shield being disposed to shield the liner and to form a second flow space within the liner, which is communicable with the combustion zone via the third mixing hole and with the first flow space via the first mixing hole.
摘要翻译：设置有燃烧区域的燃烧器被设置并且包括环形衬套，其具有在第一轴向位置处限定在其中的第一混合孔，流动套筒，在第二轴向位置具有限定在其中的第二混合孔，所述衬套在所述衬套的外部形成第一流动空间，在所述第二轴向位置处联接到所述流动套筒的端口，所述端口构造成经由所述第二混合孔从所述第一流动空间移除空气;以及屏蔽件，在第二轴向位置处具有限定在其中的第三混合孔，所述屏蔽件设置成屏蔽衬套并且在衬套内形成第二流动空间，其可经由第三混合孔和第一流动空间与燃烧区域连通通过第一混合孔。

5. 发明授权

US08683808B2 Late lean injection control strategy 有权
标题翻译：迟精注射控制策略
公开(公告)号：US08683808B2
公开(公告)日：2014-04-01
申请号：US12349869
申请日：2009-01-07
申请人： Krishna Kumar Venkataraman , Lewis Berkley Davis, Jr.
发明人： Krishna Kumar Venkataraman , Lewis Berkley Davis, Jr.
IPC分类号： F02C7/228 , F23R3/34 , F23R3/36
CPC分类号： F23R3/346 , F02C7/228 , F02C9/28
摘要： A gas turbine engine is provided and includes a 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, 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, and a control system coupled to the fuel circuit and configured to control relative amounts of the first and second fuels supplied by the fuel circuit to the first and second interiors.
摘要翻译：提供一种燃气涡轮发动机并且包括具有第一内部的燃烧器，其中由燃料回路供应到其中的第一燃料是可燃的，涡轮机，过渡区域，包括第二内部，其中燃料回路供应到其中的第二燃料并且第一燃料的燃烧产物是可燃的，多个燃料喷射器在结构上由过渡区域支撑并且联接到燃料回路，并被构造成在任何一个中将第二燃料供应到第二内部单个轴向级，多个轴向级，单个轴向圆周级和多个轴向圆周级的控制系统，以及耦合到燃料回路并被配置为控制由燃料回路供应到第一和第二燃料电路的第一和第二燃料的相对量和第二内饰。

6. 发明授权

US08631639B2 System and method of cooling turbine airfoils with sequestered carbon dioxide 失效
标题翻译：用隔热二氧化碳冷却涡轮机翼的系统和方法
公开(公告)号：US08631639B2
公开(公告)日：2014-01-21
申请号：US12413854
申请日：2009-03-30
申请人： Andres Garcia-Crespo , Lewis Berkley Davis, Jr. , George Martin Gilchrist, III , Amit Toprani
发明人： Andres Garcia-Crespo , Lewis Berkley Davis, Jr. , George Martin Gilchrist, III , Amit Toprani
IPC分类号： F02C7/16
CPC分类号： F01D25/12 , F01D5/081 , F02C1/08 , F02C3/34 , F02C6/18 , F02C7/18 , F05D2260/232
摘要： A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide from a carbon dioxide source and a method of using a stream of carbon dioxide to cool hot gas path components. The turbine power generating system includes a compressor, a combustor, a turbine, a generator, and at least one shaft linking the compressor and turbine and generator together such that mechanical energy produced from the turbine is used to drive the compressor and the generator. Carbon dioxide that is sequestered from the exhaust of the turbine may be stored and injected back into the turbine to cool hot gas path components of the turbine.
摘要翻译：具有由来自二氧化碳源的二氧化碳流提供的具有增强的冷却的涡轮发电系统以及使用二氧化碳流来冷却热气体路径部件的方法。涡轮发电系统包括压缩机，燃烧器，涡轮机，发电机以及连接压缩机和涡轮机和发电机的至少一个轴，使得从涡轮机产生的机械能被用于驱动压缩机和发电机。从涡轮机的排气隔离的二氧化碳可以被储存并注入到涡轮机中以冷却涡轮机的热气体路径部件。

7. 发明授权

US08457861B2 Late lean injection with adjustable air splits 有权
标题翻译：延迟注射，可调节空气分流
公开(公告)号：US08457861B2
公开(公告)日：2013-06-04
申请号：US13594255
申请日：2012-08-24
申请人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
发明人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
IPC分类号： F02C7/26 , G06F19/00
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors 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, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.
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第一燃料可燃的燃烧器，至少可燃第一燃料的燃烧产物的涡轮机，包括第二内部的过渡区域，其中第二燃料和第一燃料的燃烧产物是可燃的;多个燃料喷射器，其构造成在单个轴向级，多个轴向级，单个轴向周向级中的任一个中将第二燃料供应到第二内部和多个轴向圆周级，压缩机，通过该压缩机将空气供应到第一和第二内部以用于其中的燃烧;以及控制系统，被配置为控制空气相对于第一和第二内部的相对量以及第一和第二内部的相对量第二燃料供应到第一和第二内部。

8. 发明授权

US08456634B2 Optical interrogation sensors for combustion control 有权
标题翻译：用于燃烧控制的光学询问传感器
公开(公告)号：US08456634B2
公开(公告)日：2013-06-04
申请号：US12484466
申请日：2009-06-15
申请人： Keith Robert McManus , Lewis Berkley Davis, Jr.
发明人： Keith Robert McManus , Lewis Berkley Davis, Jr.
IPC分类号： G01N21/00
CPC分类号： G01N21/72 , F02C9/00 , F02D41/1451 , F23N5/082 , F23N2029/00 , F23N2041/20
摘要： Certain embodiments of the invention may include systems and methods for providing optical interrogation sensors for combustion control. According to an example embodiment of the invention, a method for controlling combustion parameters associated with a gas turbine combustor is provided. The method can include providing an optical path through the gas turbine combustor, propagating light along the optical path, measuring absorption of the light within the gas turbine combustor, and controlling at least one of the combustion parameters based at least in part on the measured absorption.
摘要翻译：本发明的某些实施例可以包括用于提供用于燃烧控制的光学询问传感器的系统和方法。根据本发明的示例性实施例，提供了一种用于控制与燃气轮机燃烧器相关联的燃烧参数的方法。该方法可以包括提供通过燃气轮机燃烧器的光路，沿着光路传播光，测量燃气轮机燃烧器内的光的吸收，以及至少部分地基于所测量的吸收来控制至少一个燃烧参数。

9. 发明授权

US08281595B2 Fuse for flame holding abatement in premixer of combustion chamber of gas turbine and associated method 失效
标题翻译：燃气轮机燃烧室预混合器火焰保护用保险丝及相关方法
公开(公告)号：US08281595B2
公开(公告)日：2012-10-09
申请号：US12128231
申请日：2008-05-28
申请人： Lewis Berkley Davis, Jr. , Stanley Kevin Widener , John Wilber
发明人： Lewis Berkley Davis, Jr. , Stanley Kevin Widener , John Wilber
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/286 , F23D14/82 , F23D2900/00015 , F23R3/343
摘要： A fuel nozzle assembly for a combustor of a gas turbine including: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front proximate to a combustion section of the combustor; an outer casing around the inner tube, wherein an air passage is defined between the outer casing and the inner tube; a gas conduit arranged in the air passage and having an outlet proximate to the front of the nozzle body, wherein fuel starts flowing through the expandable conduit only after a flashback condition occurs in the combustor, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein the gas conduit has an inlet open to the premix fuel passage.
摘要翻译：一种用于燃气轮机的燃烧器的燃料喷嘴组件，包括：喷嘴体，其具有限定通过所述喷嘴主体延伸的燃料通道的前部管和内部管，其中所述前部靠近所述燃烧器的燃烧部分; 围绕所述内管的外壳，其中在所述外壳和所述内管之间限定空气通道; 布置在所述空气通道中并且具有靠近所述喷嘴主体的前部的出口的气体导管，其中仅在所述燃烧器中发生回火状态之后燃料开始流过所述可膨胀导管，以及预燃燃料通道和将燃料喷射到燃烧器的预混合部分，其中气体管道具有通向预混合燃料通道的入口。

10. 发明授权

US08275533B2 Late lean injection with adjustable air splits 有权
标题翻译：延迟注射，可调节空气分流
公开(公告)号：US08275533B2
公开(公告)日：2012-09-25
申请号：US13345362
申请日：2012-01-06
申请人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
发明人： Lewis Berkley Davis, Jr. , Krishna Kumar Venkataraman , Willy Steve Ziminsky , Geoffrey David Myers
IPC分类号： G06F19/00 , G06F7/00
CPC分类号： F02C7/22 , F23N2041/20 , F23R3/34
摘要： A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors 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, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.
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第一燃料可燃的燃烧器，至少可燃第一燃料的燃烧产物的涡轮机，包括第二内部的过渡区域，其中第二燃料和第一燃料的燃烧产物是可燃的;多个燃料喷射器，其构造成在单个轴向级，多个轴向级，单个轴向周向级中的任一个中将第二燃料供应到第二内部和多个轴向圆周级，压缩机，通过该压缩机将空气供应到第一和第二内部以用于其中的燃烧;以及控制系统，被配置为控制空气相对于第一和第二内部的相对量以及第一和第二内部的相对量第二燃料供应到第一和第二内部。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式