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. 发明专利

JP2011064452A Gas turbine combustion dynamics control system 审中-公开
标题翻译：气体涡轮机燃烧动力学控制系统
公开(公告)号：JP2011064452A
公开(公告)日：2011-03-31
申请号：JP2010206291
申请日：2010-09-15
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SINGH KAPIL KUMAR , HAN FEI , SRINIVASAN SHIVA , KIM KWANWOO , PREETHAM , ZHANG QINGGUO , BETHKE SVEN GEORG
IPC分类号： F23R3/48 , F02C7/24 , F02C9/00 , F23R3/18 , F23R3/28
CPC分类号： F23R3/48 , F23N2041/20 , Y02T50/677
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustion dynamics control system.
SOLUTION: The system (50) includes a gas turbine combustor (52) having a plurality of combustor cans (58), crossfire tubes (54) for connecting the combustor cans (58), and a tubular connection system (56) connecting the combustor cans (58) to control combustion dynamics. The tubular connection system (56) includes tubes (60) for connecting at least a pair of the combustor cans (58).
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供燃气轮机燃烧动力学控制系统。解决方案：系统（50）包括具有多个燃烧器罐（58）的燃气轮机燃烧器（52），用于连接燃烧器罐（58）的交火管（54）和管状连接系统（56）连接燃烧器罐（58）以控制燃烧动力学。管状连接系统（56）包括用于连接至少一对燃烧器罐（58）的管（60）。版权所有（C）2011，JPO＆INPIT

2. 发明专利

JP2011047401A System and method for controlling combustion dynamics of gas turbine 有权
标题翻译：用于控制燃气涡轮机燃烧动力学的系统和方法
公开(公告)号：JP2011047401A
公开(公告)日：2011-03-10
申请号：JP2010184513
申请日：2010-08-20
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SINGH KAPIL KUMAR , HAN FEI , SRINIVASAN SHIVA , KIM KWANWOO , BALASUBRAMANYAM PREETHAM , ZHANG QINGGUO
IPC分类号： F02C7/228 , F02C7/22 , F23R3/28 , F23R3/46
CPC分类号： F23R3/46 , F23N5/242 , F23N2037/02 , F23R3/28 , F23R2900/00013
摘要： PROBLEM TO BE SOLVED: To provide a system and a method for controlling combustion dynamics of a gas turbine by changing a fuel nozzle impedance between various nozzle groups.
SOLUTION: The combustor (10) suppresses combustion emissions to the minimum, in combustion dynamics under a combustor uniform fuel split condition at a level lower than a level achievable under the combustor uniform fuel split condition by a multi-fuel nozzle type combustor using a common nozzle fuel impedance for all of nozzles, by changing the fuel impedance through geometric change or inert material addition in various nozzle groups while releasing combustion emissions at approximately the same level.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种通过改变各喷嘴组之间的燃料喷嘴阻抗来控制燃气轮机的燃烧动力学的系统和方法。解决方案：燃烧器（10）在燃烧器均匀燃料分解状态下的燃烧动力学中将燃烧排放抑制在最低水平，其水平低于通过多燃料喷嘴型燃烧器在燃烧器均匀燃料分解状态下可实现的水平通过在各种喷嘴组中通过几何变化或惰性材料添加改变燃料阻抗，同时在大致相同的水平上释放燃烧排放，对所有喷嘴使用公共喷嘴燃料阻抗。版权所有（C）2011，JPO＆INPIT

3. 发明专利

JP2010175243A System and method for reducing combustion dynamics in turbomachine 审中-公开
标题翻译：用于减少涡轮机燃烧动力学的系统和方法
公开(公告)号：JP2010175243A
公开(公告)日：2010-08-12
申请号：JP2010014925
申请日：2010-01-27
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SINGH KAPIL KUMAR , KOTHNUR VASANTH SRINIVASA , HAN FEI
IPC分类号： F23R3/16 , F02C3/30 , F23R3/32
CPC分类号： F23R3/286 , F23R3/00 , F23R2900/00013
摘要： PROBLEM TO BE SOLVED: To provide a means for reducing combustion dynamics of a turbomachine. SOLUTION: This turbomachine includes a combustion chamber (48), and at least one pre-mixer (38, 39) mounted on the combustion chamber (48). The at least one pre-mixer (38, 39) includes a body (40, 41) having a first end portion (42, 43) that extends to a second end portion (44, 45). The first end portion (42, 43) is configured to receive an amount of fuel and an amount of air and the second end portion (44, 45) defines an exit plane from which a fuel-air mixture discharges into the combustion chamber (48). The turbomachine also includes a combustion dynamics reduction system (90) operatively coupled to the at least one pre-mixer (38, 39). The combustion dynamics reduction system (90) includes at least one of a boundary layer perturbation mechanism and an acoustic wave introduction system which disrupt a flow pattern of the fuel-air mixture within the at least one pre-mixer (38, 39). COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于减少涡轮机的燃烧动力学的方法。解决方案：该涡轮机包括燃烧室（48）和安装在燃烧室（48）上的至少一个预混合器（38,39）。所述至少一个预混合器（38,39）包括具有延伸到第二端部部分（44,45）的第一端部部分（42,43）的主体（40,41）。第一端部（42,43）被构造成容纳一定量的燃料和一定量的空气，而第二端部（44,45）限定了一个出口平面，燃料 - 空气混合物从该出口平面排放到燃烧室（48 ）。涡轮机还包括可操作地耦合到至少一个预混合器（38,39）的燃烧动力学降低系统（90）。燃烧动力学降低系统（90）包括边界层扰动机构和声波引入系统中的至少一个，其破坏所述至少一个预混合器（38,39）内的燃料 - 空气混合物的流动模式。版权所有（C）2010，JPO＆INPIT

4. 发明专利

JP2011069358A Mode decoupling for every can using fuel division on can level 有权
标题翻译：可以在CAN水平上使用燃油部分的模式解除
公开(公告)号：JP2011069358A
公开(公告)日：2011-04-07
申请号：JP2010202531
申请日：2010-09-10
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： NARRA VENKATESWARLU , DAVIS LEWIS BERKELY JR , HAN FEI , KIM KWANWOO , SINGH KAPIL KUMAR , SRINIVASAN SHIVA KUMAR , VENKATARAMAN KRISHNA K
IPC分类号： F02C7/228 , F23R3/28 , F23R3/46
CPC分类号： F02C7/228 , F02C9/26 , F05D2270/14
摘要： PROBLEM TO BE SOLVED: To provide detuning of can combustor and decoupling of frequency by a multi-circuit fuel manifold.
SOLUTION: A gas turbine system (100) is provided. The gas turbine system (100) includes: a compressor (110) structured to compress air (115); and a combustor can (120) in flow communication with the compressor (110). The combustor can (120) is structured to receive the compressed air (115) from the compressor (110) and to burn a fuel flow. The gas turbine system (100) can include multi-circuit manifolds (200, 300) coupled to the combustor can (120) and structured to provide a divided fuel flow from the fuel flow to the combustor can (120).
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供罐式燃烧器的失谐和通过多回路燃料歧管对频率的去耦。解决方案：提供一种燃气轮机系统（100）。燃气轮机系统（100）包括：构造成压缩空气（115）的压缩机（110）; 和与压缩机（110）流体连通的燃烧室（120）。燃烧室（120）构造成从压缩机（110）接收压缩空气（115）并燃烧燃料流。燃气轮机系统（100）可以包括耦合到燃烧器罐（120）并被构造成提供从燃料流到燃烧器罐（120）的分开的燃料流的多回路歧管（200,300）。版权所有（C）2011，JPO＆INPIT

5. 发明专利

JP2011002220A Resonator assembly for mitigating dynamics in gas turbine 有权
标题翻译：用于减轻气体涡轮动力学的共振器组件
公开(公告)号：JP2011002220A
公开(公告)日：2011-01-06
申请号：JP2010135646
申请日：2010-06-15
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： DAVIS JR LEWIS BERKLEY , HAN FEI , SRINIVASAN SHIVA , SINGH KAPIL KUMAR , KIM KWANWOO , NARRA VENKATESWARLU
IPC分类号： F23R3/16 , F23R3/50
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00013 , F23R2900/00014
摘要： PROBLEM TO BE SOLVED: To provide a resonator assembly for mitigating dynamics in gas turbines.SOLUTION: A combustor (24) for a gas turbine engine (10) and its related method are provided in which a plurality of combustor cans (26) are selectively adapted with corresponding resonators. The resonators may, for example, be attached to every combustor can (500-534) in the consecutive arrangement of the combustor cans, every other can (400-416), every third can (600-612) or the like, and may be tuned to the same or first, second, third, etc. frequencies of operation. Such selective tuning is configured to suppress one or more of out-of-phase and in-phase dynamic interaction of streams discharged from adjacent combustor cans by changing the frequencies of pressure oscillation instabilities across the arrangement of adjacent combustor cans.
摘要翻译：要解决的问题：提供一种用于减轻燃气轮机动力学的谐振器组件。解决方案：提供一种用于燃气涡轮发动机（10）的燃烧器（24）及其相关方法，其中多个燃烧器罐（26）选择性地适应相应的谐振器。谐振器可以例如在燃烧器罐的连续布置中，每隔一个（400-416），每三分之一罐（600-612）等连接到每个燃烧室（500-534），并且可以调整到相同或第一，第二，第三等操作频率。这种选择性调谐被配置为通过改变相邻燃烧器罐的布置的压力振荡不稳定性的频率来抑制从相邻燃烧器罐排出的流的异相和同相动态相互作用中的一个或多个。

6. 发明专利

JP2010261434A Method for detecting gas turbine flashback 有权
标题翻译：检测气体涡轮发生器的方法
公开(公告)号：JP2010261434A
公开(公告)日：2010-11-18
申请号：JP2010044836
申请日：2010-03-02
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SINGH KAPIL KUMAR , VARATHARAJAN BALACHANDER , KRAEMER GILBERT OTTO , YILMAZ ERTAN , LACY BENJAMIN PAUL
IPC分类号： F02C9/00 , F02C7/00
CPC分类号： F02C9/00 , F05D2260/80 , F05D2270/71 , F23N5/082 , F23N5/242 , F23N2041/20 , Y02T50/677
摘要： PROBLEM TO BE SOLVED: To provide a method for monitoring and controlling a gas turbine. SOLUTION: This method comprises steps of: predicting (86) frequencies of combustion dynamics in a combustor (14) using operating conditions (40) of a gas turbine (10); receiving (88) a signal (38) from a sensor (36) that is indicative of combustion dynamics in the combustor (14); and detecting (94) a flashback if a frequency of the received signal does not correspond to the predicted frequencies. The method may further include a step (84) of acquiring operating conditions of the gas turbine (10) in real time. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于监测和控制燃气轮机的方法。解决方案：该方法包括以下步骤：使用燃气轮机（10）的操作条件（40）预测（86）燃烧器（14）中的燃烧动态的频率（86）。从传感器（36）接收（88）信号（38），所述传感器指示所述燃烧器（14）中的燃烧动力学; 并且如果接收信号的频率不对应于预测频率，则检测（94）闪回。该方法还可以包括实时获取燃气涡轮机（10）的运行状况的步骤（84）。版权所有（C）2011，JPO＆INPIT

7. 发明专利

JP2012102733A System and method for combustion dynamics control by acoustic control/cancellation of fuel flow fluctuation at fuel injection location 审中-公开
标题翻译：燃油喷射位置燃油流动波动控制/消除燃烧动力控制系统与方法
公开(公告)号：JP2012102733A
公开(公告)日：2012-05-31
申请号：JP2011244050
申请日：2011-11-08
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： SINGH KAPIL KUMAR , HAN FEI , SRINIVASAN SHIVA , SRINIVASAN SHIVA , KIM KWANWOO , BALASUBRAMANYAM PREETHAM , QINGGUO ZHANG
IPC分类号： F02C9/28 , F02C7/00 , F02C9/00 , F23R3/28 , F23R3/30
CPC分类号： F02C7/228 , F02C9/50 , F05D2260/96 , F05D2270/14 , F23N5/16 , F23N5/24 , F23R2900/00013 , Y02T50/677
摘要： PROBLEM TO BE SOLVED: To provide a combustion dynamics control system that includes a fuel injector configured to receive a premixed fuel via a fuel injection orifice, and an acoustic driver configured to drive fuel flow perturbations across a fuel injection orifice to substantially zero.SOLUTION: The combustion dynamics control system for aviation or power-generation gas turbine engines employs an acoustic driver 50 configured to drive fuel flow perturbations across the entire of a premixed fuel injection orifice 52 to substantially zero in response to a control signal. The combustion dynamics control system includes: a sensor 60 configured to measure acoustic pressure across the fuel injection orifice 52 and generate a signal therefrom; a signal conditioner 62 configured to condition the sensor signal and generate a conditioned sensor signal therefrom; and a controller 64 configured to generate the acoustic driver control signal in response to the conditioned sensor signal.
摘要翻译：要解决的问题：提供一种燃烧动态控制系统，其包括配置成经由燃料喷射孔接收预混合燃料的燃料喷射器，以及配置成驱动燃料喷射孔周围的燃料流扰动基本为零的声学驱动器。解决方案：用于航空或发电燃气涡轮发动机的燃烧动力学控制系统采用声学驱动器50，声学驱动器50被配置为响应于控制信号将整个预混合燃料喷射孔52的燃料流动扰动驱动到基本为零。燃烧动力学控制系统包括：传感器60，被配置为测量燃料喷射孔52两端的声压并从其产生信号; 信号调节器62，被配置为调节传感器信号并从其生成调节的传感器信号; 以及控制器64，被配置为响应于经调节的传感器信号产生声学驱动器控制信号。版权所有（C）2012，JPO＆INPIT

8. 发明专利

JP2011247263A Turbomachine fuel nozzle 审中-公开
标题翻译：涡轮燃料喷嘴
公开(公告)号：JP2011247263A
公开(公告)日：2011-12-08
申请号：JP2011117652
申请日：2011-05-26
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： KHAN ABDUL RAFEY , SINGH KAPIL KUMAR
IPC分类号： F02C9/28 , F23R3/28
CPC分类号： F23D11/24 , F23D11/38 , F23D2900/14482 , F23R3/28
摘要： PROBLEM TO BE SOLVED: To achieve a low level of NOx emissions.SOLUTION: A fuel nozzle 20 of a combustor includes a flow passage 84 including a body having a first end 91 that extends to a second end 92 through flow channels 101, 102, 103, and 104 having flow areas. A fuel inlet 95 is provided at the first end 91 of the body 88. A fuel outlet 96 is provided at the second end 92 of the body 88. Control flow passages 130 and 131 are fluidly connected to the body 88 between the first and second ends, and are configured and disposed to deliver a control flow into the fuel nozzle 20. The control flow establishes a selectively variable effective flow area of the flow passage 84.
摘要翻译：要解决的问题：实现低水平的NOx排放。解决方案：燃烧器的燃料喷嘴20包括流路84，流路84包括具有第一端91的主体，第一端91通过具有流动区域的流动通道101,102,103和104延伸到第二端92。燃料入口95设置在主体88的第一端91处。燃料出口96设置在主体88的第二端92处。控制流动通道130和131在第一和第二之间流体地连接到主体88 并且被配置和设置成将控制流输送到燃料喷嘴20中。控制流建立了流动通道84的选择性可变的有效流动面积。（C）2012年，JPO和INPIT

9. 发明专利

JP2011137629A FUEL SYSTEM ACOUSTIC FEATURE TO MITIGATE COMBUSTION DYNAMICS FOR MULTI-NOZZLE DRY LOW NOx COMBUSTION SYSTEM 有权
标题翻译：燃油系统消声功能，用于减轻多喷嘴低NOx燃烧系统的燃烧动力
公开(公告)号：JP2011137629A
公开(公告)日：2011-07-14
申请号：JP2010285235
申请日：2010-12-22
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： KIM KWANWOO , SINGH KAPIL KUMAR , HAN FEI , SRINIVASAN SHIVA
IPC分类号： F23R3/20 , F02C7/22 , F02C7/228 , F23R3/28
CPC分类号： F02C7/228 , F02C7/22 , F05D2240/128 , F05D2270/082 , F23R3/28 , F23R2900/00014 , Y10T29/49826
摘要： PROBLEM TO BE SOLVED: To solve the problem, wherein in a dry low NOx combustor, combustion dynamics are concerned as an element which may inhibit the activity of a system, shorten the service lives of components and reduce relative durability and fluctuation of air fuel ratio causes fluctuation of heat release amount, leading to continuance of the combustion dynamics as a result, and to provide a system for mitigating the combustion dynamics. SOLUTION: A dry low NOx fuel nozzle 10 includes: one or more downstream orifices 20 formed to define a first fluid flow passage 21 along which fluid is directed to flow; an upstream orifice 40, located upstream from the downstream orifices 20, formed to define a second fluid flow passage 41 along which the fluid is directed to flow; and connecting passages 50, disposed to fluidly couple the first and second fluid flow passages of the downstream and upstream orifices, respectively, to one another. At least one of a radial size and an axial location of the upstream orifice 40 is set to cooperatively detune an acoustic impedance of a fuel system. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：解决的问题为了解决在干式低NOx燃烧器中的燃烧动力学作为可能抑制系统的活性的因素，缩短部件的使用寿命并降低相对耐久性和波动的问题空燃比导致放热量的波动，结果导致燃烧动力学的持续性，并且提供用于减轻燃烧动态的系统。干燥的低NOx燃料喷嘴10包括：一个或多个下游孔口20，其形成为限定流体被引导流动的第一流体流动通道21; 位于下游孔20上游的上游孔40形成为限定流体被引导流过的第二流体流动通道41; 以及连接通道50，其设置成将下游和上游孔的第一和第二流体流动通道彼此流体地联接。上游孔40的径向尺寸和轴向位置中的至少一个被设定为协调地使燃料系统的声阻抗失谐。版权所有（C）2011，JPO＆INPIT

10. 发明专利

JP2010261699A System and method for controlling combustion dynamics 有权
标题翻译：用于控制燃烧动力学的系统和方法
公开(公告)号：JP2010261699A
公开(公告)日：2010-11-18
申请号：JP2010096577
申请日：2010-04-20
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： SINGH KAPIL KUMAR , HAN FEI , SRINIVASAN SHIVA , KIM KWANWOO
IPC分类号： F23K5/00 , F02C7/22 , F02C9/28 , F23C15/00
CPC分类号： F23D14/48 , F02C7/222 , F02C9/28 , F05D2260/964 , F23D2900/14482 , F23N5/24 , F23R2900/00013
摘要： PROBLEM TO BE SOLVED: To provide a fail-safe and synchronization-type system for controlling combustion dynamics in a combustor, and its method. SOLUTION: The control system 22 includes a fuel supply passage 24 having an inlet part 26, a first split flow part 28, a second split flow part 30, and an outlet part 34. The first split flow part 28 includes a first length and a first diameter. The second split flow part 30 includes a second length and a second diameter, and is arranged to be spaced from the first split flow part 28. The first/second split flow parts 28, 30 join together at a merging position 32. The outlet part 34 is connected to the merging position 32 of the first/second split flow parts 28, 30. At least one of flow rate adjustment devices 36, 38 is connected to the inlet part 26, and fuel flow is split alternately to the first/second split flow parts 28, 30 to generate fuel flow perturbation at the merging position 32. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于控制燃烧器中的燃烧动力学的故障安全和同步型系统及其方法。解决方案：控制系统22包括具有入口部分26，第一分流部分28，第二分流部分30和出口部分34的燃料供给通道24.第一分流部分28包括第一长度和第一直径。第二分流部30包括第二长度和第二直径，并且布置成与第一分流部28间隔开。第一/第二分流部28,30在合流位置32处接合在一起。出口部 34连接到第一/第二分流部分28,30的合并位置32.流量调节装置36,38中的至少一个连接到入口部分26，并且燃料流被交替地分裂成第一/第二分流分流流动部分28,30，以在合并位置32产生燃料流动扰动。版权所有（C）2011，JPO＆INPIT

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