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1. 发明专利

JP2011085385A Fuel nozzle seal 审中-公开
标题翻译：燃油喷嘴密封
公开(公告)号：JP2011085385A
公开(公告)日：2011-04-28
申请号：JP2010232056
申请日：2010-10-15
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： STOIA LUCAS JOHN , NEGRONI ALBERTO
IPC分类号： F23R3/28 , F01D11/00 , F02C7/28
CPC分类号： F23R3/283 , F23R2900/00012
摘要： PROBLEM TO BE SOLVED: To provide a fuel nozzle (100) corresponding to axial thermal growth, having an ultra-low leakage speed, being robust in vibration environment and having further improved durability. SOLUTION: The fuel nozzle (100) can include: a plurality of concentric tubular bodies (110); and one or more of lip seals (170) positioned between a pair of the plurality of concentric tubular bodies. A fuel nozzle assembly can include a fuel nozzle end cap assembly and the plurality of concentric tubular bodies mounted to the fuel nozzle end cap assembly. The one or more of seal lips can be positioned between the fuel nozzle end cap assembly and the concentric tubular bodies. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供对应于轴向热生长的燃料喷嘴（100），其具有超低的泄漏速度，在振动环境中是坚固的并且具有进一步改善的耐久性。燃料喷嘴（100）可以包括：多个同心管状体（110）; 以及位于一对多个同心管状体之间的一个或多个唇形密封件（170）。燃料喷嘴组件可以包括燃料喷嘴端盖组件和安装到燃料喷嘴端帽组件上的多个同心管状体。密封唇中的一个或多个可以位于燃料喷嘴端盖组件和同心管状体之间。版权所有（C）2011，JPO＆INPIT

2. 发明专利

JP2011085383A High strength crossover manifold and joining method 审中-公开
标题翻译：高强度绞车管道和接头方法
公开(公告)号：JP2011085383A
公开(公告)日：2011-04-28
申请号：JP2010229216
申请日：2010-10-12
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： STOIA LUCAS JOHN
IPC分类号： F23R3/28 , F02C7/00
CPC分类号： F23R3/60 , F23R3/48 , F23R2900/00017 , Y10T29/49229
摘要： PROBLEM TO BE SOLVED: To provide a high strength crossover manifold and a joining method used for a gas turbine fuel nozzle. SOLUTION: Within a secondary fuel nozzle (38), a plurality of tubular bodies (48, 50, 52, 62) axially extending downstream define passages (54, 56, 60, 64) operable to allow a flow of fluid to flow through each of the passages (54, 56, 60, 64) and the passages (54, 56, 60, 64) include the outermost tertiary passage (54) and a radially inward secondary fuel passage (56). A fuel peg (40) extending radially outwardly from the axially extending tubular bodies (48, 50, 52, 62) emits fluid radially outwardly therefrom. The crossover manifold (58) attached to the fuel peg (40) and in fluid communication with the radially inward secondary fuel passage (56) and the fuel peg (40) is attached to the corresponding tubular bodies (48, 50, 52) defining the tertiary passage (54) and the radially inward secondary fuel passage (56) by butt welding (66). COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于燃气轮机燃料喷嘴的高强度交叉歧管和接合方法。解决方案：在次级燃料喷嘴（38）内，在下游轴向延伸的多个管状体（48,50,52,62）限定通道（54,56,60,64），其可操作以允许流体流动流过每个通道（54,56,60,64）并且通道（54,56,60,64）包括最外面的第三通道（54）和径向向内的副燃料通道（56）。从轴向延伸的管状体（48,50,52,62）径向向外延伸的燃料栓（40）从其径向向外发射流体。附接到燃料栓（40）并与径向向内的副燃料通道（56）和燃料栓（40）流体连通的交叉歧管（58）附接到相应的管状体（48,50,52），所述管状体第三通道（54）和径向向内的二次燃料通道（56）通过对接焊接（66）。版权所有（C）2011，JPO＆INPIT

3. 发明专利

JP2011140952A Fuel nozzle for turbine engine with passive purge air passageway 审中-公开
标题翻译：燃油喷嘴用于无人驾驶空气通风的涡轮发动机
公开(公告)号：JP2011140952A
公开(公告)日：2011-07-21
申请号：JP2010289834
申请日：2010-12-27
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： INTILE JOHN , POPOVIC PREDRAG , STOIA LUCAS JOHN
IPC分类号： F02C7/18 , F02C7/22 , F23R3/06 , F23R3/12 , F23R3/16
CPC分类号： F23R3/283 , F23D2209/30 , F23D2214/00
摘要： PROBLEM TO BE SOLVED: To provide a fuel nozzle such that the nozzle itself is not subjected to extremely high temperatures, because as for a fuel nozzle for a turbine engine, during some turbine operational conditions, purge air passageways of the fuel nozzle are temporarily prevented from conducting a flow of cooling air, and in those situations, portions of the fuel nozzles adjacent combustion zones are likely to be subjected to extremely high temperatures that can damage the fuel nozzles.
SOLUTION: A second fuel nozzle 100 for the turbine includes a passive purge air passageway 110 for providing purge air to the second fuel nozzle 100 when the nozzle is in operation. The passive purge air passageway 110 draws in air from a location 162 adjacent an upstream end of the nozzle. Because of a pressure differential between air located at the downstream end of the nozzle and air located at the upstream end of the nozzle, purge air will run through the passive purge air passageway at all times when the nozzle is in operation. There is no need for a supply of compressed purge air.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了提供一种燃料喷嘴，使得喷嘴本身不受到极高的温度，因为对于用于涡轮发动机的燃料喷嘴，在一些涡轮机操作条件期间，燃料喷嘴的吹扫空气通道临时防止冷却空气流动，在这些情况下，邻近燃烧区域的燃料喷嘴的部分容易受到可能损坏燃料喷嘴的极高温度的影响。用于涡轮机的第二燃料喷嘴100包括被动吹扫空气通道110，用于在喷嘴运行时向第二燃料喷嘴100提供净化空气。被动吹扫空气通道110从邻近喷嘴的上游端的位置162吸入空气。由于位于喷嘴下游端的空气和位于喷嘴上游端的空气之间的压力差，当喷嘴运行时，净化空气将始终穿过被动吹扫空气通道。不需要供应压缩的吹扫空气。版权所有（C）2011，JPO＆INPIT

4. 发明专利

JP2011085142A Fuel nozzle seal spacer and method of installing the same 有权
标题翻译：燃油喷嘴密封件及其安装方法
公开(公告)号：JP2011085142A
公开(公告)日：2011-04-28
申请号：JP2010232057
申请日：2010-10-15
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： STOIA LUCAS JOHN , SUBRAMANIAN KARTHIK
IPC分类号： F02C7/28 , F01D11/00 , F02C7/00
CPC分类号： F02C7/22 , F05D2230/60 , F05D2240/55 , F23R3/283 , F23R2900/00012
摘要： PROBLEM TO BE SOLVED: To provide a method of mounting lip seals (170) within a sleeve assembly (265) of a fuel nozzle (100).
SOLUTION: The method may include the steps of sliding a first lip seal (320) along a second diameter tube (290) until the first lip seal (320) is brought into contact with a first tube flange (310) of a first diameter tube (280), sliding a seal spacer (270) along the second diameter tube (290) until the seal spacer (270) is brought into contact with the first lip seal (320), and sliding a second lip seal (350) along the second diameter tube (290) until the second lip seal (350) is brought into contact with the seal spacer (270).
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种将唇形密封件（170）安装在燃料喷嘴（100）的套筒组件（265）内的方法。解决方案：该方法可以包括以下步骤：沿着第二直径管（290）滑动第一唇形密封件（320），直到第一唇形密封件（320）与第一密封件（320）的第一管状凸缘（310）接触第一直径管（280），沿着第二直径管（290）滑动密封间隔件（270），直到密封间隔件（270）与第一唇形密封件（320）接触，并且滑动第二唇形密封件）直到第二唇形密封件（350）与密封垫片（270）接触。版权所有（C）2011，JPO＆INPIT

5. 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

6. 发明专利

JP2014132214A Fuel injector for supplying fuel to combustor 审中-公开
标题翻译：燃油喷射器供应给燃油的燃料
公开(公告)号：JP2014132214A
公开(公告)日：2014-07-17
申请号：JP2013270677
申请日：2013-12-27
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： CAI JUN , BOARDMAN GREGORY ALLEN , STOIA LUCAS JOHN , KARIM HASAN
IPC分类号： F23R3/14 , F23R3/20 , F23R3/30
CPC分类号： F23R3/346 , F23C2900/07001 , F23R3/14 , F23R3/286
摘要： PROBLEM TO BE SOLVED: To provide a fuel injector for a combustor.SOLUTION: A fuel injector for a combustor generally includes an annular outer body having an inlet and an outlet. The outer body at least partially defines an outer flow passage. An inner flow passage extends at least partially through the outer flow passage and a radial swirler is disposed at the inlet of the outer body. The radial swirler includes a first radial passage separated from a second radial passage. The first radial passage has a first plurality of swirler vanes, and the second radial passage has a second plurality of swirler vanes. The first radial passage is in communication with the outer flow passage, and the second radial passage is in communication with the inner flow passage.
摘要翻译：要解决的问题：提供一种用于燃烧器的燃料喷射器。解决方案：用于燃烧器的燃料喷射器通常包括具有入口和出口的环形外部主体。外体至少部分地限定外部流动通道。内部流动通道至少部分地延伸穿过外部流动通道，并且径向旋流器设置在外部主体的入口处。径向旋流器包括与第二径向通道分离的第一径向通道。第一径向通道具有第一多个旋流器叶片，并且第二径向通道具有第二多个旋流器叶片。第一径向通路与外流路连通，第二径向通路与内流路连通。

7. 发明专利

JP2014095546A Enhancement for fuel injector 审中-公开
标题翻译：燃油喷射器增强
公开(公告)号：JP2014095546A
公开(公告)日：2014-05-22
申请号：JP2013227816
申请日：2013-11-01
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： STOIA LUCAS JOHN , BOARDMAN GREGORY ALLEN , CHEN WEI
IPC分类号： F23R3/16 , F02C7/232 , F23R3/12 , F23R3/20 , F23R3/30
CPC分类号： F02C7/22 , F23R3/28 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To increase a degree of mixing of combustible materials to achieve completed combustion processes.SOLUTION: A fuel injector 30 is provided and includes a surface 31 disposed proximate to a flow 32 of a first fluid, and a delta wing feature 33. The surface 31 has an upstream portion 34 and a downstream portion 35 defined relative to the flow and defines an injector hole 36 in the downstream portion 35, the hole 36 permitting a jet of a second fluid to be injected into the flow 32. The delta wing feature 33 is disposed on the surface 31 at the upstream portion 34 and is configured to lift an oncoming portion of the flow 32 off the surface 31 and to cause the oncoming portion of the flow 32 to form a pair of counter-rotating vortices that respectively rotate with the jet 37 in a cross-flow direction.
摘要翻译：要解决的问题：增加可燃材料的混合程度以实现完成的燃烧过程。解决方案：设置燃料喷射器30并且包括靠近第一流体的流32设置的表面31和三角翼特征33 表面31具有相对于流动限定的上游部分34和下游部分35，并且在下游部分35中限定了喷射器孔36，孔36允许将第二流体的射流注入到流动部分32中。三角翼部件33在上游部分34处设置在表面31上，并且构造成将流动物体32的迎面的部分从表面31提升，并且使得流动部分32的迎面的部分形成一对反向旋转涡流其分别与喷射器37在横流方向上旋转。

8. 发明专利

JP2013221735A Method, system, and apparatus for transition piece contouring 有权
标题翻译：方法，系统和设备的过渡层结构
公开(公告)号：JP2013221735A
公开(公告)日：2013-10-28
申请号：JP2013081701
申请日：2013-04-10
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： DICINTIO RICHARD MARTIN , MELTON PATRICK BENEDICT , STOIA LUCAS JOHN
IPC分类号： F23R3/42 , F01D25/00 , F02C7/00
CPC分类号： F01D9/023 , F05D2230/00 , F05D2250/70 , G06F17/5009 , G06F17/5086 , G06F2217/80 , Y10T29/49234
摘要： PROBLEM TO BE SOLVED: To provide an apparatus, method and system for transition piece contouring, which reduce damage, since a hot combustion gas flowing through a transition piece of a gas turbine subjects a duct structure to very high temperatures and can lead the duct structure to premature deterioration that requires repair and replacement thereof.SOLUTION: A high-temperature section and a low-temperature section of a transition piece area determined, and the low-temperature section is contoured before the high-temperature section. The low-temperature section of the transition piece may be contoured to intercept a hot gas flow.
摘要翻译：要解决的问题：为了提供一种用于过渡件轮廓加工的装置，方法和系统，其减少损坏，因为流过燃气轮机的过渡片的热燃烧气体将管道结构对接到非常高的温度并且可以引导管道结构过早变质，需要修理和更换。解决方案：确定过渡段面积的高温段和低温段，低温段在高温段之前形成轮廓。过渡件的低温部分可以是轮廓以拦截热气流。

9. 发明专利

JP2013190198A System for supplying working fluid to combustor 有权
标题翻译：向工厂供应工作流体的系统
公开(公告)号：JP2013190198A
公开(公告)日：2013-09-26
申请号：JP2013044911
申请日：2013-03-07
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： CHEN WEI , STOIA LUCAS JOHN , DICINTIO RICHARD MARTIN
IPC分类号： F23R3/06 , F02C7/22 , F23R3/10 , F23R3/28
CPC分类号： F23R3/045 , F01D9/023 , F23C6/047 , F23R3/283 , F23R3/346
摘要： PROBLEM TO BE SOLVED: To provide a system for supplying a working fluid to a combustor.SOLUTION: A system includes a combustion chamber, a liner that circumferentially surrounds at least a part of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a part of the liner. A tube provides fluid communication for the working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube spirals between the flow sleeve and the liner.
摘要翻译：要解决的问题：提供一种用于向燃烧器供应工作流体的系统。解决方案：系统包括燃烧室，周向围绕燃烧室的至少一部分的衬套和至少周向包围的流动套筒班轮的一部分。管提供流体连通以使工作流体流过流动套管和衬套并进入燃烧室，并且管在流动套筒和衬套之间螺旋。

10. 发明专利

JP2013140003A Turbine engine and method for flowing air in turbine engine 有权
标题翻译：涡轮发动机及其在涡轮发动机中流动空气的方法
公开(公告)号：JP2013140003A
公开(公告)日：2013-07-18
申请号：JP2012275235
申请日：2012-12-18
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： STOIA LUCAS JOHN , MELTON PATRICK BENEDICT , POPOVIC PREDRAG PEJA
IPC分类号： F23R3/26 , F02C7/22 , F02C9/20 , F02C9/50 , F23R3/04
CPC分类号： F23R3/045 , F23R3/26
摘要： PROBLEM TO BE SOLVED: To provide a turbine engine and a method for flowing air in a turbine engine.SOLUTION: A gas turbine engine includes a combustor, a fuel nozzle placed in an end of the combustor, and a passage configured to receive an air flow from a compressor discharge casing. The passage directs the air flow into a chamber downstream of the nozzle. A chamber pressure is lower than a compressor discharge casing pressure. The gas turbine engine also includes a flow control device configured to control the air flow from the compressor discharge casing into the passage.
摘要翻译：要解决的问题：提供一种涡轮发动机和用于使涡轮发动机中的空气流动的方法。解决方案：燃气涡轮发动机包括燃烧器，设置在燃烧器的端部的燃料喷嘴和构造成接收空气的通道从压缩机排放套管流出。通道将空气流引导到喷嘴下游的腔室中。室压力低于压缩机排气套管压力。燃气涡轮发动机还包括流量控制装置，该流量控制装置被配置为控制从压缩机排放壳体进入通道的空气流。

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