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1. 发明专利

JP2005291496A Hybrid seal, system and method for incorporating this hybrid seal 审中-公开
标题翻译：混合密封件，混合密封件的系统和方法
公开(公告)号：JP2005291496A
公开(公告)日：2005-10-20
申请号：JP2005097998
申请日：2005-03-30
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： BHATE NITIN , CHUPP RAYMOND EDWARD , BRUCE KEVIN , NEGRONI ALBERTO JOSE , CAIRO RONALD RALPH
IPC分类号： F01D11/00 , F01D5/20 , F01D11/02 , F01D11/10 , F01D11/12 , F01D11/22 , F01D25/00 , F01D25/12 , F02C7/12 , F02C7/28 , F16J15/06 , F16J15/46
CPC分类号： F16J15/46 , F01D11/005 , F01D11/025 , F01D11/22 , F05D2240/11 , F05D2240/55
摘要： PROBLEM TO BE SOLVED: To provide a hybrid seal for sealing an adjacent component of a turbine engine.
SOLUTION: This system has a first structure 16 communicating with a first structure 16, and a second structure 18 for storing a seal assembly 20 between the first structure 16 and the second structure 18. The seal assembly 20 includes an interface seal 24 arranged in contact with the first structure 16, and a deflection seal 26 pressurized and energized by contacting with the second structure 18 and the interface seal 24 by a second medium 30.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供用于密封涡轮发动机的相邻部件的混合密封件。解决方案：该系统具有与第一结构16连通的第一结构16和用于在第一结构16和第二结构18之间存储密封组件20的第二结构18.密封组件20包括界面密封件24 布置成与第一结构16接触;以及偏转密封件26，通过第二介质30与第二结构18和界面密封件24接触而被加压和激励。版权所有（C）2006，JPO＆NCIPI

2. 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

3. 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

4. 发明专利

JP2007163125A Fuel nozzle, gas turbine combustor, and method for independent pilot fuel control in secondary fuel nozzle 有权
标题翻译：燃油喷嘴，燃气轮机，以及二次燃油喷嘴中独立导弹燃料控制的方法
公开(公告)号：JP2007163125A
公开(公告)日：2007-06-28
申请号：JP2006334071
申请日：2006-12-12
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： VANDALE DANIEL D , SIMONS DERRICK , NEGRONI ALBERTO JOSE , ROMOSER CAREY
IPC分类号： F23R3/28 , F02C7/228 , F02C7/232 , F02C9/40 , F23R3/34
CPC分类号： F23C6/047 , F23D2209/30 , F23D2900/00008 , F23D2900/00015 , F23D2900/14004 , F23L7/002 , F23R3/346
摘要： PROBLEM TO BE SOLVED: To provide a fuel nozzle with optimized operability by reducing the discharge. SOLUTION: Disclosed herein is a fuel nozzle 36. The fuel nozzle 36 includes a first fuel introduction location, a second fuel introduction location, and fuel passages 50. The first fuel introduction location is located radially about the fuel nozzle 36 and is connected with the fuel passage 50. The second fuel introduction location is located at an end of the fuel nozzle 36 and is connected with another fuel passage 50 such that the fuel passage 50 connected to the first fuel introduction location is separate from the fuel passage 50 connected to the second fuel introduction location. COPYRIGHT: (C)2007,JPO&INPIT
摘要翻译：要解决的问题：通过减少放电来提供具有优化的可操作性的燃料喷嘴。本发明公开了一种燃料喷嘴36.燃料喷嘴36包括第一燃料引入位置，第二燃料引入位置和燃料通道50.第一燃料引入位置位于燃料喷嘴36的径向周围，并且是与燃料通道50连接。第二燃料引入位置位于燃料喷嘴36的一端并与另一个燃料通道50连接，使得连接到第一燃料引入位置的燃料通道50与燃料通道50分离连接到第二燃料引入位置。版权所有（C）2007，JPO＆INPIT

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