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1. 发明专利

JP2009047413A Leakage reducing venturi for dry low nitrogen oxide (nox) combustor 审中-公开
标题翻译：降低低氧氮氧化物（NOX）燃烧器的泄漏泄漏
公开(公告)号：JP2009047413A
公开(公告)日：2009-03-05
申请号：JP2008208309
申请日：2008-08-13
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： GROOMS NEAL WILLIAM , LEBEGUE JEFFREY SCOTT , SIMONS DERRICK W
IPC分类号： F23R3/16 , F23R3/42
CPC分类号： F23R3/002 , F23R3/04 , F23R3/286
摘要： PROBLEM TO BE SOLVED: To provide a leakage reducing venturi (18) for a dry low nitrogen oxide (NOx) emission combustor (10).
SOLUTION: The venturi (18) includes a substantially annular outer liner (42); a substantially annular inner liner (44); a venturi channel (46) defined by the annular inner liner (44) and the annular outer liner (42) and including a front end (48) and a rear end (50); a front weld part (52) disposed in proximity to the front end (48) of the venturi channel (46) and configured to connect the annular outer liner (42) with the annular inner liner (44); and a rear weld part (54) disposed in proximity to the rear end (50) of the venturi channel (46) and configured to connect the annular outer liner (42) with the annular inner liner (44).
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：为干燥的低氮氧化物（NOx）发射燃烧器（10）提供一种泄漏降低文丘里管（18）。解决方案：文丘里管（18）包括基本上环形的外衬套（42）; 大致环形的内衬（44）; 由环形内衬（44）和环形外衬（42）限定的包括前端（48）和后端（50）的文丘里通道（46）。设置在文丘里通道（46）的前端（48）附近并被构造成将环形外衬套（42）与环形内衬（44）连接的前焊接部分（52）; 以及靠近文丘里通道（46）的后端（50）设置并构造成将环形外衬套（42）与环形内衬（44）连接的后焊接部分（54）。版权所有（C）2009，JPO＆INPIT

2. 发明专利

JP2009198171A Gas turbine combustor flame stabilizer 审中-公开
标题翻译：燃气轮机燃烧器火焰稳定器
公开(公告)号：JP2009198171A
公开(公告)日：2009-09-03
申请号：JP2009034691
申请日：2009-02-18
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： SIMONS DERRICK W , MYERS GEOFFREY D , THOMAS LARRY L , LEBEGUE JEFFREY
IPC分类号： F23R3/18 , F02C7/00 , F23R3/30 , F23R3/34 , F23R3/42
CPC分类号： F23R3/18 , F23M20/00 , F23M2900/13002 , F23R3/286
摘要： PROBLEM TO BE SOLVED: To present a stabilizer absorbing heat from a heat flux generated within a combustor and maintaining a temperature sufficient to sustain ignition of a flame. SOLUTION: A secondary fuel nozzle 16 is disposed proximately to a combustion chamber 12 to discharge fuel 54 at the combustion chamber 12. The stabilizer 32 is disposed at the secondary fuel nozzle 16 so as to be positioned in close proximity to a flame when the fuel 54 at the secondary fuel nozzle 16 is ignited. The stabilizer 32 is composed of a material having the ability to absorb heat from the heat flux generated within the combustor 10 and maintaining a temperature sufficient to sustain ignition of the flame. COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种从燃烧器内产生的热通量吸收热量的稳定剂并保持足以维持火焰点燃的温度。解决方案：副燃料喷嘴16靠近燃烧室12设置，以便在燃烧室12排放燃料54.稳定器32设置在次级燃料喷嘴16处以便靠近火焰定位当二次燃料喷嘴16处的燃料54被点燃时。稳定器32由具有从燃烧器10内产生的热通量吸收热量并保持足以维持火焰点燃的温度的材料构成。版权所有（C）2009，JPO＆INPIT

3. 发明专利

JP2009019869A Apparatus/method for cooling combustion chamber/venturi in low nox combustor 审中-公开
标题翻译：用于冷却低NOX COMBUSTOR燃烧室/ VENTURI的装置/方法
公开(公告)号：JP2009019869A
公开(公告)日：2009-01-29
申请号：JP2008179661
申请日：2008-07-10
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： SIMONS DERRICK W , HESSLER WILLIAM KIRK , GROOMS NEAL , LEBEGUE JEFFREY
IPC分类号： F23R3/06 , F02C7/18 , F23R3/18 , F23R3/30 , F23R3/42
CPC分类号： F23R3/286 , F23R3/002 , F23R2900/03044
摘要： PROBLEM TO BE SOLVED: To provide an apparatus capable of reducing emissions of nitrogen oxides in a gas turbine combustion system.
SOLUTION: A dry NOx emission combustor 30 includes a premixing chamber 36 for mixing fuel with cooling gas and a combustion chamber 32 positioned downstream of the premixing chamber 36 for the combustion of pre-mixed fuel and cooling gas. The combustor 30 further includes a venturi 46 which is positioned between the premixing chamber 36 and the combustion chamber 32 and has annular walls including converging and diverging wall portions 41, 43 defining a constricted portion and through which the premixed fuel and air pass to the combustion chamber 32. The walls define a passage 44 where cooling gas flows along the combustion chamber 32 and have an exit 64 for flowing cooling gas to inside of the combustion chamber 32. A plurality of inlets 56 at the converging and diverging wall portions 41, 43 ingest cooling gas into the passage 44 to produce an impingement cooling effect. A plurality of turbulators 62 disposed downstream of the inlets 56 interact with the cooling gas to produce a turbulent cooling effect. The combustor 30 is effectively fired over a temperature range to reduce the NOx emissions of the combustor 30.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种能够减少燃气轮机燃烧系统中氮氧化物排放的装置。解决方案：干式NOx排放燃烧器30包括用于将燃料与冷却气体混合的预混合室36和位于预混合室36下游的用于燃烧预混燃料和冷却气体的燃烧室32。燃烧器30还包括文丘里管46，该文丘里管46位于预混合室36和燃烧室32之间，并且具有环形壁，其包括限定收缩部分的会聚和发散的壁部分41,43，并且预混燃料和空气通过燃烧器壁32限定了通道44，其中冷却气体沿着燃烧室32流动，并且具有用于使冷却气体流到燃烧室32内部的出口64.多个入口56在会聚和发散的壁部分41,43 将冷却气体吸入通道44以产生冲击冷却效果。设置在入口56下游的多个紊流器62与冷却气体相互作用以产生湍流冷却效果。燃烧器30在温度范围内被有效地燃烧，以减少燃烧器30的NOx排放。版权所有：（C）2009，JPO＆INPIT

4. 发明专利

JP2005155622A Fuel split control method for gas turbine combustor 审中-公开
标题翻译：燃气轮机燃油分配控制方法
公开(公告)号：JP2005155622A
公开(公告)日：2005-06-16
申请号：JP2004336214
申请日：2004-11-19
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： HEALY TIMOTHY A , SIMONS DERRICK W
IPC分类号： F02C9/00 , F02C9/28 , F23N1/00 , F23R3/34
CPC分类号： F02C9/28 , F05D2270/08 , F05D2270/112 , F05D2270/303 , F23N1/002 , F23N2023/08 , F23N2025/06 , F23N2025/21 , F23N2025/26 , F23N2041/20 , F23R3/34 , Y10T477/40
摘要： PROBLEM TO BE SOLVED: To provide a method for determining a target exhaust gas temperature 70 for a gas turbine, relating to a combustor control algorithm for fuel split and nitrogen oxide/nitrogen dioxide (NOx) levelling. SOLUTION: The method for determining the target exhaust gas temperature comprises a step of determining the target exhaust gas temperature 70 in accordance with the pressure conditions of a compressor, a step of determining a temperature control amount for the target exhaust gas temperature in accordance with at least one parameter of a parameter group consisting of specific humidity 68, compressor inlet pressure loss 52 and turbine back pressure 56, and a step of controlling the target exhaust gas temperature by the application of the temperature control amount. COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于确定用于燃气轮机的目标排气温度70的方法，涉及用于燃料分配和氮氧化物/二氧化氮（NOx））流平的燃烧器控制算法。解决方案：用于确定目标排气温度的方法包括根据压缩机的压力条件确定目标排气温度70的步骤，确定目标排气温度的温度控制量的步骤根据由特定湿度68，压缩机入口压力损失52和涡轮背压56组成的参数组的至少一个参数，以及通过施加温度控制量来控制目标排气温度的步骤。版权所有（C）2005，JPO＆NCIPI

5. 发明专利

JP2010181141A Burner tube of combustion system 审中-公开
标题翻译：燃烧管燃烧系统
公开(公告)号：JP2010181141A
公开(公告)日：2010-08-19
申请号：JP2010017526
申请日：2010-01-29
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： SIMONS DERRICK W , ZVEDENUK LEONID , MESHKOV SERGEY ANATOLIEVICH , MITROFANOV VALERY
IPC分类号： F23R3/18 , F23R3/14 , F23R3/28 , F23R3/32
CPC分类号： F23R3/14 , F23D14/64
摘要： PROBLEM TO BE SOLVED: To provide a combustor having burner tubes supplied with combustion fuel from a fuel supply system.
SOLUTION: Axial swirlers 116 are installed inside the burner tubes 120, 122, 126. The burner tubes are made to be flare-type tubes at the downstream of the swirlers. This structure extends lean blowout and low frequency dynamics margins to improve combustion stability, which further decreases NOx emission. The combustor includes the burner tubes supplied with combustion fuel from the fuel supply system, and the axial swirlers installed inside the burner tubes. The burner tubes are made to be flare-type tubes at the downstream of the swirlers.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种具有从燃料供应系统供给燃烧燃料的燃烧器管的燃烧器。解决方案：轴向旋流器116安装在燃烧器管120,122,126的内部。燃烧器管在旋流器的下游被制成为耀斑型管。这种结构延长了精益喷吹和低频动态裕度，以提高燃烧稳定性，进一步降低NOx排放。燃烧器包括从燃料供应系统供应燃烧燃料的燃烧器管和安装在燃烧器管内的轴向旋流器。燃烧器管在旋流器的下游被制成为耀斑型管。版权所有（C）2010，JPO＆INPIT

6. 发明专利

JP2010060275A Turning angle of secondary fuel nozzle for turbomachinery combustor 审中-公开
标题翻译：涡轮燃烧器燃油喷嘴的转角
公开(公告)号：JP2010060275A
公开(公告)日：2010-03-18
申请号：JP2009199151
申请日：2009-08-31
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： SIMONS DERRICK W , NEGRONI ALBERTO JOSE , THOMAS LARRY LOU , LEBEGUE JEFFREY SCOTT
IPC分类号： F23R3/14 , F02C7/22 , F23R3/28 , F23R3/34
CPC分类号： F23R3/14 , F23D2900/14701 , F23R3/286 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To provide an improved turbomachinery combustor having a turning angle.
SOLUTION: This combustor 10 includes: a primary combustion chamber 12; a secondary combustion chamber 14; one or more primary nozzles 24 disposed in the primary combustion chamber 12 to supply fuel to the primary combustion chamber 12; a center body assembly 30; a Venturi 16 disposed downstream from the center body assembly 30; and a secondary fuel nozzle 40 housed in the center body assembly 30 and extended toward the Venturi 16 to supply fuel to the secondary combustion chamber 14. The secondary fuel nozzle 40 includes: a fuel passage 44; an air passage 46; and a swirler 100 disposed in the periphery of the fuel passage 44 and having one or more vanes 105 projected in the radial direction in the air passage 46. Each vane 105 has a rear edge 110 formed at a turning angle to the longitudinal axis of the secondary fuel nozzle 40, and the turning angle exceeds 45°.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供具有转向角的改进的涡轮机械燃烧器。解决方案：该燃烧器10包括：主燃烧室12; 二次燃烧室14; 设置在主燃烧室12中以将主燃料室12供给燃料的一个或多个主喷嘴24; 中心体组件30; 文丘里16布置在中心体组件30的下游; 以及容纳在中心主体组件30中并且朝向文氏管16延伸以将燃料供应到二次燃烧室14的二次燃料喷嘴40.辅助燃料喷嘴40包括：燃料通道44; 空气通道46; 以及设置在燃料通道44的周边并且具有在空气通道46中沿径向突出的一个或多个叶片105的旋流器100.每个叶片105具有后边缘110，后边缘110形成为与次级燃料喷嘴40，转向角度超过45°。版权所有（C）2010，JPO＆INPIT

7. 发明专利

JP2008101898A Mixing hole arrangement and method for improving homogeneity of air and fuel mixture in combustor 有权
标题翻译：混合孔布置方法和改进空气和燃料混合物在燃烧器中的均匀性的方法
公开(公告)号：JP2008101898A
公开(公告)日：2008-05-01
申请号：JP2007231052
申请日：2007-09-06
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： POPOVIC PREDRAG , SIMONS DERRICK W , VENKATARAMAN KRISHNA K
IPC分类号： F23R3/06 , F02C9/16
CPC分类号： F23R3/286 , F23R3/10
摘要： PROBLEM TO BE SOLVED: To improve homogeneity of an air and fuel mixture in a combustor. SOLUTION: The mixing hole arrangement 26 for improving homogeneity of the air and fuel mixture in the combustor includes a plurality of mixing holes 26 defined by a liner 12, wherein at least one of the plurality of mixing holes 18 is at least one of sized and positioned to impede penetration of a fluid flow into a primary mixing zone located in a head end of the combustor. The impeding mixing hole 18 can allow penetration of the fluid flow up to a maximum of 165% into the primary mixing zone. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提高燃烧器中空气和燃料混合物的均匀性。解决方案：用于改善燃烧器中空气和燃料混合物的均匀性的混合孔装置26包括由衬套12限定的多个混合孔26，其中多个混合孔18中的至少一个是至少一个其尺寸和位置阻止流体流入位于燃烧器头端的主混合区中。阻碍混合孔18可以允许流体流最多165％渗入主混合区。版权所有（C）2008，JPO＆INPIT

8. 发明专利

JP2006214436A Venturi for combustor 有权
标题翻译： VENTURI FOR COMBUSTOR
公开(公告)号：JP2006214436A
公开(公告)日：2006-08-17
申请号：JP2006020017
申请日：2006-01-30
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： SIMONS DERRICK W , AMOND THOMAS C III , GUPTA AJAY K
IPC分类号： F02C7/18 , F23R3/06
CPC分类号： F23M5/085 , F23C6/047 , F23R3/005 , F23R3/346 , F23R2900/03041
摘要： PROBLEM TO BE SOLVED: To provide a combustion chamber inboard radial damper venturi for a gas turbine.
SOLUTION: This venturi includes a contraction part 66, an expansion part 68 and a cylinder part 59, and includes a double wall surface venturi chamber 60 defining a venturi section in which compressed air, fuel and combustion product flows to a downstream through the contraction part, the expansion part and the cylinder part, a cooling gas passage 64 between wall surfaces of the venturi chamber, at least one cooling gas inlet 72 on an outer wall surface of the venturi chamber, and at least one cooling gas outlet 74 on an inner wall surface of the venturi chamber and at least in one of the expansion part and the cylinder part, and in a downstream of at least one of the cooling gas inlets and upstream of an axial direction end part 76 of the chamber.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：为燃气轮机提供内侧径向阻尼文丘里管的燃烧室。解决方案：该文丘里管包括收缩部分66，膨胀部分68和气缸部分59，并且包括限定文丘里管部分的双壁表面文丘里腔室60，压缩空气，燃料和燃烧产物流入下游收缩部分，膨胀部分和圆筒部分，文丘里室的壁表面之间的冷却气体通道64，文丘里室的外壁表面上的至少一个冷却气体入口72和至少一个冷却气体出口74 在文丘里管室的内壁表面上，并且至少在膨胀部分和气缸部分中的一个以及冷却气体入口中的至少一个和腔室的轴向端部76的上游的下游。版权所有（C）2006，JPO＆NCIPI

9. 发明专利

JP2005265403A Turbine combustor transferring component having dilution hole 审中-公开
标题翻译：具有稀释孔的涡轮搅拌机输送组件
公开(公告)号：JP2005265403A
公开(公告)日：2005-09-29
申请号：JP2005074259
申请日：2005-03-16
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： SIMONS DERRICK W , GUPTA AJAY KUMAR , ROMOSER CAREY EDWARD
IPC分类号： F23R3/06 , F01D9/02 , F02C7/18 , F23R3/00 , F23R3/42
CPC分类号： F01D9/023 , F05D2270/082
摘要： PROBLEM TO BE SOLVED: To provide a transferring component having a dilution hole useful for promoting the dilution and mixing, and reducing emission.
SOLUTION: A transferring component main body 18 comprising an inlet end part 20 for receiving a combustion product from a turbine combustor and an outlet end part 22 for allowing a gaseous product to flow in a nozzle of first stage 14, has the dilution holes 28 in areas 24, 26 respectively adjacent to the inlet and outlet end parts of the transferring component main body. The amounts of diluted air flowing in a gas flow at the inlet and outlet end parts of the transferring component are approximately equal to each other. Positions and sizes of the holes are respectively indicated by X, Y and Z coordinates and hole diameters in a table I. The X and Y coordinates are positioned in a circular plane of the transferring component main body at the inlet end parts, and the Z coordinate is extended in the direction of gas flow from an original point.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供具有用于促进稀释和混合的稀释孔的转印组分，并减少发光。解决方案：包括用于从涡轮机燃烧器接收燃烧产物的入口端部20和用于允许气态产物在第一级14的喷嘴中流动的出口端部22的转移部件主体18具有稀释分别与转印部件主体的入口端部和出口端部分相邻的区域24,26中的孔28。在转移部件的入口端部和出口端部处的气流中流动的稀释空气的量大致相等。孔的位置和尺寸分别由表I中的X，Y和Z坐标和孔直径表示.X和Y坐标位于入口端部处的转印部件主体的圆形平面中，Z 坐标从原点延伸到气流的方向。版权所有（C）2005，JPO＆NCIPI

10. 发明专利

JP2011141111A Turbo machine nozzle 审中-公开
标题翻译：涡轮喷嘴
公开(公告)号：JP2011141111A
公开(公告)日：2011-07-21
申请号：JP2010285237
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： BENJAMIN MARC LIONEL , ROMIG BRYAN WESLEY , SIMONS DERRICK W , STOIA LUCAS JOHN
IPC分类号： F23R3/28 , F02C7/18 , F23R3/14 , F23R3/34
CPC分类号： F23R3/28 , F01D9/023 , F02C7/12 , F02C7/18 , F02C7/22 , F05D2260/14 , F23R3/14
摘要： PROBLEM TO BE SOLVED: To cool a swirler hub of a tip of an injection nozzle assembly mounted in a combustor of a gas turbine. SOLUTION: The injection nozzle assembly 38 includes a swirler member 117 provided with a hub portion 120 having an internal surface 121. The injection nozzle assembly 38 also includes a nozzle section 85, and a nozzle tip member 124 fluidly coupled to the nozzle section 85 and the swirler member 117. The nozzle tip member 124 includes a body having a first end section that extends from the nozzle section 85 to a second end section arranged in the hub portion 120 of the swirler member 117. The nozzle tip member includes an external surface, and a discharge port. At least one of the external surface of the nozzle tip member 124 and the internal surface 121 of the swirler member 117 hub portion 120 is provided with a plurality of grooves. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：冷却安装在燃气轮机的燃烧器中的喷嘴组件的尖端的旋流器毂。注射喷嘴组件38包括设置有具有内表面121的轮毂部分120的旋流器构件117.喷射喷嘴组件38还包括喷嘴部分85和与喷嘴流体连接的喷嘴尖端部件124 部分85和旋流器构件117.喷嘴末端构件124包括具有从喷嘴部分85延伸到设置在旋流器构件117的毂部120中的第二端部的第一端部的主体。喷嘴尖端构件包括外表面和排出口。喷嘴头构件124的外表面和旋流器构件117毂部120的内表面121中的至少一个设置有多个凹槽。版权所有（C）2011，JPO＆INPIT

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