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1. 发明专利

JP2009257747A Combustor of turbine, method for retro-fitting combustor of turbine, and method for constructing combustor of turbine 审中-公开
标题翻译：涡轮搅拌机，重新搭载涡轮搅拌机的方法，以及构造涡轮搅拌机的方法
公开(公告)号：JP2009257747A
公开(公告)日：2009-11-05
申请号：JP2009092608
申请日：2009-04-07
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： HESSLER WILLIAM , POPOVIC PREDRAG
IPC分类号： F23R3/10 , F01D25/00 , F02C7/00
CPC分类号： F23R3/06 , F23R3/26 , F23R2900/00016 , Y10T29/49346
摘要： PROBLEM TO BE SOLVED: To provide a combustor of a turbine, a method for retro-fitting the combustor of the turbine, and a method for constructing the combustor of the turbine. SOLUTION: The combustor includes a combustion chamber along which a dilution breach is formed; a casing perimetrically surrounding the combustion chamber to form an airflow between the casing and the combustion chamber, the airflow being configured to supply dilution air to the combustion chamber via the dilution breach; and an easily adjustable dilution airflow tuning part disposed on the casing and in communication with the airflow. The dilution airflow tuning part is configured to increase and/or decrease an available amount of the dilution air to be supplied to the combustion chamber. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种涡轮机的燃烧器，一种用于重新安装该涡轮机的燃烧器的方法，以及一种用于构造该涡轮机的燃烧器的方法。解决方案：燃烧器包括燃烧室，沿着该燃烧室形成稀释破裂; 围绕所述燃烧室的壳体，以在所述壳体和所述燃烧室之间形成气流，所述气流被配置为经由所述稀释破坏来向所述燃烧室供应稀释空气; 以及容易调节的稀释气流调节部件，其设置在壳体上并与气流连通。稀释气流调节部分被配置为增加和/或减少要供应到燃烧室的稀释空气的可用量。版权所有（C）2010，JPO＆INPIT

2. 发明专利

JP2010190567A System, method, and apparatus for providing secondary fuel nozzle assembly 审中-公开
标题翻译：用于提供二次燃油喷嘴总成的系统，方法和装置
公开(公告)号：JP2010190567A
公开(公告)日：2010-09-02
申请号：JP2010030785
申请日：2010-02-16
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： HESSLER WILLIAM KIRK , LOWE RICHARD GENE , POPOVIC PREDRAG
IPC分类号： F23R3/42 , F02C7/20 , F02C7/22 , F23R3/28 , F23R3/34
CPC分类号： F23R3/343
摘要： PROBLEM TO BE SOLVED: To provide a secondary fuel nozzle assembly preventing a failure due to thermal expansion in a combustor for a gas turbine.
SOLUTION: The secondary fuel nozzle assembly 100 includes: a central portion 102 for forming a proximal end 108, a distal end 110, and a central passage 152, and including a coil tube 150 extending from the proximal end 108 to the distal end 110 through the central passage 152; a flange 106 having a main secondary fuel orifice in fluid communication with the central passage 152 at the proximal end 108 and a pilot orifice 202 in fluid communication with the coil tube 150 at the proximal end 108; and a tip portion 104 having a proximal end 108 and a distal end 110 and forming a passage passing through the chip part 104. The passage includes the distal end 110 of the coil tube 150 and the chip part 104 in fluid communication with an orifice formed at the distal end 110 of the chip part 104. The coil tube 150 effectively reduces a failure caused by thermal stress.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种二次燃料喷嘴组件，其防止由于燃气轮机的燃烧器中的热膨胀引起的故障。第二燃料喷嘴组件100包括：用于形成近端108的中心部分102，远端110和中心通道152，并且包括从近端108延伸到远端的线圈管150 端部110穿过中央通道152; 具有与近端108处的中心通道152流体连通的主次级燃料孔的凸缘106和在近端108与线圈管150流体连通的导向孔202; 以及具有近端108和远端110并形成通过芯片部分104的通道的尖端部分104.该通道包括线圈管150的远端110和与形成的孔流体连通的芯片部分104 在芯片部分104的远端110处。线圈管150有效地减少了由热应力引起的故障。版权所有（C）2010，JPO＆INPIT

3. 发明专利

JP2010032208A Center body cap for turbomachine combustor and method 有权
标题翻译：用于涡轮搅拌机和方法的中心体阀
公开(公告)号：JP2010032208A
公开(公告)日：2010-02-12
申请号：JP2009171689
申请日：2009-07-23
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 , HESSLER WILLIAM KIRK , VENKATARAMAN KRISHNA KUMAR
IPC分类号： F23R3/28 , F23R3/06 , F23R3/14 , F23R3/32 , F23R3/34
CPC分类号： F23R3/005 , F23R3/045 , F23R3/14 , F23R3/283 , F23R3/286 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a technology for improving the control and flame stability of the discharge of a turbomachine combustor. SOLUTION: The turbomachine includes a combustor assembly, a cap assembly attached to the combustor assembly, a center body 54 in the cap assembly, a wall 57 of the center body having a first end 59, a second end 60 and an intermediate portion 61, and an external turbulator member 75 in operable communication with the cap assembly. The external turbulator member is spaced from the wall to form a passage 78 defined by a gap between the wall of the center body and the external turbulator. The external turbulator member includes a step 88 positioned at the second end of the center body. The step defines a radial distance around the second end of the center body. The external turbulator member is formed having a step-to-gap ratio relative to the center body in a range of about 0.8 to about 1.2. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于改善涡轮机燃烧器的排放的控制和火焰稳定性的技术。解决方案：涡轮机包括燃烧器组件，附接到燃烧器组件的帽组件，帽组件中的中心体54，中心体的壁57具有第一端59，第二端60和中间体部分61和与盖组件可操作地连通的外部湍流器构件75。外部紊流器构件与壁间隔开以形成由中心体的壁和外部湍流器之间的间隙限定的通道78。外部紊流器构件包括位于中心体的第二端的台阶88。该步骤限定围绕中心体的第二端的径向距离。在约0.8至约1.2的范围内形成具有相对于中心体的台间间隙比的外部紊流器构件。版权所有（C）2010，JPO＆INPIT

4. 发明专利

JP2010025543A Gas turbine transition piece having dilution hole 审中-公开
标题翻译：具有稀释孔的气体涡轮转换装置
公开(公告)号：JP2010025543A
公开(公告)日：2010-02-04
申请号：JP2009170734
申请日：2009-07-22
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： VENKATARAMAN KRISHNA K , HESSLER WILLIAM KIRK , POPOVIC PREDRAG
IPC分类号： F23R3/06 , F02C7/22 , F23R3/18 , F23R3/42
CPC分类号： F01D9/023 , F05D2250/74 , F23R3/06
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine transition piece. SOLUTION: This gas turbine transition piece 16 includes a duct body having a front end part 26 and a rear end part 28, and the duct body forms an enclosure for closing a flow of a combustion product from a combustor 10 to a turbine first-stage nozzle 18. A plurality of dilution holes 32 is formed inside the duct body, and is installed in an (X, Y, Z)coordinate position measured from a zero reference point in the center of an outlet plane of the transition piece. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种燃气轮机过渡件。解决方案：该燃气轮机过渡件16包括具有前端部26和后端部28的管道主体，并且管道主体形成用于将燃烧产物从燃烧器10流动到涡轮机第一级喷嘴18.多个稀释孔32形成在管体内部，并且安装在从过渡件的出口平面的中心的零参考点测量的（X，Y，Z）坐标位置。版权所有（C）2010，JPO＆INPIT

5. 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

6. 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

7. 发明专利

JP2011038766A Integral liner and venturi for eliminating air leakage 审中-公开
标题翻译：消除空气泄漏的整体衬套和通风口
公开(公告)号：JP2011038766A
公开(公告)日：2011-02-24
申请号：JP2010181516
申请日：2010-08-16
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： HESSLER WILLIAM KIRK , LEBEGUE JEFFREY , POPOVIC PREDRAG , PAQUIN TODD DANIEL
IPC分类号： F23R3/42 , F02C7/22 , F02C7/28 , F23R3/06
CPC分类号： F23R3/002 , F23R2900/00016
摘要： PROBLEM TO BE SOLVED: To provide a combustion liner assembly for a gas turbine combustor.
SOLUTION: The combustion liner assembly includes: a plurality of fuel nozzles (16) disposed circumferentially about a central axis of the combustor; and a venturi section (18) disposed downstream of the fuel nozzles (16) and connected to a head end (62) of the liner assembly. The venturi section (18) defines an annular throat area (32) downstream of the fuel nozzles (16). A liner sleeve (14) is connected to and commences at a downstream end of the venturi section (18). At least a portion of the venturi section (18) serves as a liner upstream of the liner sleeve (14).
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烧器的燃烧衬套组件。燃烧衬套组件包括：围绕燃烧器的中心轴线周向设置的多个燃料喷嘴（16）; 以及布置在燃料喷嘴（16）下游并连接到衬套组件的头端部（62）的文氏管部分（18）。文丘里管部分18限定在燃料喷嘴16的下游的环形喉部区域32。衬套（14）连接到文丘里管部分（18）的下游端并开始。文氏管部分（18）的至少一部分用作衬套（14）上游的衬垫。版权所有（C）2011，JPO＆INPIT

8. 发明专利

JP2010048250A Method and device for assembling gas turbine engine 有权
标题翻译：用于组装气体涡轮发动机的方法和装置
公开(公告)号：JP2010048250A
公开(公告)日：2010-03-04
申请号：JP2009188802
申请日：2009-08-18
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： HESSLER WILLIAM KIRK , POPOVIC PREDRAG , CHEN WEI A , DAVIS TONY KEITH
IPC分类号： F02C7/18 , F01D25/00 , F01D25/12 , F01D25/14 , F02C7/00
CPC分类号： F02C7/18 , F01D9/023 , Y10T29/49245
摘要： PROBLEM TO BE SOLVED: To provide a combustor assembly 104 used for a gas turbine engine 100. SOLUTION: This combustor assembly includes a combustor liner 106 in fluid communication with a transition piece 118, and a flow device. The flow device includes a first part 122 of a dimension at least partially extending to the periphery of the combustion liner, and a second part 124 joined to the first part of the flow device and extending from the first part of the flow device. The second part of the flow device extends at least partially to the periphery of at least a part of the transition piece, and the second part of the flow device includes a scoop 125 forming a single cooling air passage 126 having single scoop-shaped opening parts 148 and 248 by cooperating with the transition piece, and the scoop is also oriented so as to introducing a substantially uniform cooling air flow to the transition piece. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供用于燃气涡轮发动机100的燃烧器组件104.解决方案：该燃烧器组件包括与过渡件118流体连通的燃烧器衬套106和流动装置。流动装置包括至少部分地延伸到燃烧衬套的周边的尺寸的第一部分122和连接到流动装置的第一部分并且从流动装置的第一部分延伸的第二部分124。流动装置的第二部分至少部分地延伸到过渡件的至少一部分的周边，并且流动装置的第二部分包括形成具有单个勺状开口部分的单个冷却空气通道126的勺子125 148和248通过与过渡件配合，并且铲斗也被定向成将大致均匀的冷却空气流引入过渡件。版权所有（C）2010，JPO＆INPIT

9. 发明专利

JP2009275701A Method and device for cooling and dilution-adjusting gas turbine combustor liner and transition piece joint part 有权
标题翻译：用于冷却和稀释调节气体涡轮机排气管和过渡连接件的方法和装置
公开(公告)号：JP2009275701A
公开(公告)日：2009-11-26
申请号：JP2009115095
申请日：2009-05-12
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： HESSLER WILLIAM K , POPOVIC PREDRAG , NYBERG CHARLES
IPC分类号： F02C7/18 , F01D25/12
CPC分类号： F23R3/06 , F23R3/002 , F23R3/26 , F23R2900/00012 , F23R2900/03042
摘要： PROBLEM TO BE SOLVED: To provide a method and a device for cooling and dilution-adjusting a gas turbine combustor liner and a transition piece joint part. SOLUTION: The combustor liner (40) includes: a front end part; a contracted diameter portion (44); and a rear end part overlapped on the contracted diameter portion and thereby having a cooling and dilution sleeve (50) formed with a cooling plenum (60) between the contracted diameter portion and it. A plurality of cooling and dilution air inlet holes (58) are formed in the cooling and dilution sleeve, and a plurality of cooling and dilution air outlet holes (62) are formed adjacent to a rear end edge part of the liner. During use, the cooling and dilution air passes through the cooling and dilution air inlet holes (58), passes and flows through the plenum (60), and flows out from the cooling and dilution air outlet holes (62). Thereby, the rear end part of the combustor liner is cooled and dilution-adjusted without removing the transition piece. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于对燃气轮机燃烧器衬套和过渡件接头部进行冷却和稀释调节的方法和装置。解决方案：燃烧器衬套（40）包括：前端部分; 收缩直径部分（44）; 并且后端部分重叠在收缩直径部分上，从而具有在收缩直径部分之间形成有冷却气室（60）的冷却和稀释套筒（50）。在冷却和稀释套筒中形成多个冷却和稀释空气入口孔（58），并且与衬套的后端边缘部分相邻地形成多个冷却和稀释空气出口孔（62）。在使用期间，冷却和稀释空气通过冷却和稀释空气入口孔（58），通过并流经通风室（60），并从冷却和稀释空气出口孔（62）流出。由此，燃烧器衬套的后端部被冷却并进行稀释调整，而不需要移除过渡件。版权所有（C）2010，JPO＆INPIT

10. 发明专利

JP2007298269A Method and device for expanding primary and secondary flames in combustor 审中-公开
标题翻译：用于扩展燃烧器中主要和次要火焰的方法和装置
公开(公告)号：JP2007298269A
公开(公告)日：2007-11-15
申请号：JP2007120450
申请日：2007-05-01
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： HESSLER WILLIAM KIRK , NEGRONI ALBERTO JOSE , POPOVIC PREDRAG , VENKATARAMAN KRISHNA K
IPC分类号： F23R3/42 , F23R3/16
CPC分类号： F23R3/16
摘要： PROBLEM TO BE SOLVED: To provide a device 42 for expanding an annular fluid flow 34 and a central fluid flow 36.
SOLUTION: The device 42 comprises a combustor 12 including a venturi 22 and a center body 24 having an upstream end and a downstream end 32, and a venturi throat 28 formed by the venturi 22 and arranged upstream at a downstream position by 0.19 inches (4.83 mm) from the downstream end 32 of the center body 24. The venturi throat 28 can be arranged at least either upstream at the downstream end 32 of the center body 24 or on the common face with the downstream end 32.
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：解决方案：提供一种用于使环形流体流34和中心流体流36膨胀的装置42.解决方案：装置42包括包括文氏管22和中心体24的燃烧器12，该中心体24具有上游端和下游端32以及由文丘里管22形成的文丘里喉部28，并且在距离中心体24的下游端部32的下游位置处布置在下游位置上方0.19英寸（4.83mm）的上游。文丘里喉部28可布置至少在中心体24的下游端32的上游，或与下游端32相同的共同面上。（C）2008，JPO＆INPIT

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