-
21.发明申请FUEL CONTROL METHOD AND FUEL CONTROL APPARATUS FOR GAS TURBINE AND GAS TURBINE 有权燃油控制方法和燃油控制装置用于气体涡轮机和气体涡轮机公开(公告)号：US20110016873A1
公开(公告)日：2011-01-27
申请号：US12671473
申请日：2009-07-01
申请人： Sosuke Nakamura , Satoshi Tanimura , Shinji Akamatsu , Shinsuke Nakamura , Takashi Sonoda , Akihiko Saito , Makoto Kishi
发明人： Sosuke Nakamura , Satoshi Tanimura , Shinji Akamatsu , Shinsuke Nakamura , Takashi Sonoda , Akihiko Saito , Makoto Kishi
摘要： A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine.
摘要翻译： 一种用于具有燃烧器的燃气轮机的燃料控制方法，所述燃气轮机由至少两组用于供应燃料的主喷嘴组成，并且在燃烧器（S1）点燃时从所有组的主喷嘴供应燃料，并且供应 在燃气轮机的后续加速期间来自组A的三个主喷嘴的燃料（S3）。 由于在加速期间从少量主喷嘴喷射燃料，所以每个主喷嘴的燃料流量增加，从而提高燃烧区域的燃料空气比（燃料流量/空气流量），提高燃烧 特点 因此，一氧化碳和未燃碳氢化合物的产生减少，由此不需要旁通阀并且降低制造成本。 因为燃料从所有组的主喷嘴供应并且在点火时在燃烧器的整个区域燃烧，所以可以容易地将火焰传播到所有其他相邻的主喷嘴组，从而提高整个燃气轮机的点火特性 。
-
公开(公告)号：US20080184708A1
公开(公告)日：2008-08-07
申请号：US11574203
申请日：2005-09-01
申请人： Atsushi Moriwaki , Masataka Ohta , Keijiro Saitoh , Satoshi Tanimura , Shinji Akamatsu , Norihiko Nagai
发明人： Atsushi Moriwaki , Masataka Ohta , Keijiro Saitoh , Satoshi Tanimura , Shinji Akamatsu , Norihiko Nagai
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23R3/12 , F23R3/343 , Y02T50/675
摘要： A gas turbine combustor includes a pilot burner, a plurality of main burners disposed around the main burners on the radially outer side. Each of the main burners (2) includes an extension tube disposed at the downstream end. The outlet of the extension tube is shaped to have a radial edge which is parallel to the radial direction. In this manner, occurrence of flashback is effectively prevented.
摘要翻译： 燃气轮机燃烧器包括引燃燃烧器，在径向外侧设置在主燃烧器周围的多个主燃烧器。 每个主燃烧器（2）包括设置在下游端的延伸管。 延伸管的出口成形为具有平行于径向方向的径向边缘。 以这种方式，有效地防止闪回的发生。
-
公开(公告)号：US20060101814A1
公开(公告)日：2006-05-18
申请号：US11266202
申请日：2005-11-04
IPC分类号： F23R3/30
摘要： In a combustor of a gas turbine which has a pilot nozzle being installed to the center of the axis of a combustor basket and a plurality of main nozzles being installed to the vicinity of the pilot nozzle and provided with a premixing tool on the outer circumference thereof, wherein, fuel being injected as air-fuel pre-mixture from the main nozzle into the interior of a transition piece forming a combustion chamber downstream of the combustor basket is ignited by diffusion flame being generated by the pilot nozzle in the transition piece so as to generate a premixed flame in the transition piece, wherein combustion is performed by a part of the plurality of main nozzles from start-up until a predetermined load rate and then performed by adding the remaining portion of the plurality of main nozzles when the predetermined load rate is exceeded.
摘要翻译： 在燃气轮机的燃烧器中，具有安装在燃烧器筐的轴心的中心的先导喷嘴，并且多个主喷嘴安装在导向喷嘴附近，并且在其外周上设置有预混合工具 其特征在于，从所述主喷嘴向所述燃烧器筐下游形成燃烧室的过渡部件的内部喷射的燃料被喷射，所述扩散火焰由所述过渡部件中的先导喷嘴产生， 以在过渡件中产生预混合的火焰，其中燃料由多个主喷嘴的一部分从起动直到预定的负载率进行，然后通过在预定的负载下加入多个主喷嘴的剩余部分 率超过。
-
公开(公告)号：US09291104B2
公开(公告)日：2016-03-22
申请号：US12743832
申请日：2008-11-19
CPC分类号： F02C7/24 , F01D25/04 , F23M20/005 , F23R3/26 , F23R2900/00014 , G10K11/161 , G10K11/172
摘要： In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.
摘要翻译： 在根据本发明的阻尼装置中，阻尼装置63安装在旁路管61上，该旁通管61向燃烧器过渡件33供给一定量的高压空气。阻尼装置63包括：流体导入单元71， 通过覆盖旁通管61的外周部分的流体引入空间B，形成共振空间Da和Db的多个声箱73a和73b，其中基部连接到流体引入单元71，并且沿着外部延伸的端部 旁通管61的圆周方向的周向部分以及通过分隔谐振空间Da和Db形成预定长度的共振管道Ea和Eb的隔板74a和74b。
-
公开(公告)号：US08408002B2
公开(公告)日：2013-04-02
申请号：US11574203
申请日：2005-09-01
申请人： Atsushi Moriwaki , Masataka Ohta , Keijiro Saitoh , Satoshi Tanimura , Shinji Akamatsu , Norihiko Nagai
发明人： Atsushi Moriwaki , Masataka Ohta , Keijiro Saitoh , Satoshi Tanimura , Shinji Akamatsu , Norihiko Nagai
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23R3/12 , F23R3/343 , Y02T50/675
摘要： A gas turbine combustor includes a pilot burner, a plurality of main burners disposed around the main burners on the radially outer side. Each of the main burners (2) includes an extension tube disposed at the downstream end. The outlet of the extension tube is shaped to have a radial edge which is parallel to the radial direction. In this manner, occurrence of flashback is effectively prevented.
摘要翻译： 燃气轮机燃烧器包括引燃燃烧器，在径向外侧设置在主燃烧器周围的多个主燃烧器。 每个主燃烧器（2）包括设置在下游端的延伸管。 延伸管的出口成形为具有平行于径向方向的径向边缘。 以这种方式，有效地防止闪回的发生。
-
26.发明授权Fuel nozzle, gas turbine combustor with the same, and gas turbine with the same 有权燃油喷嘴，燃气轮机与燃气轮机相同，与燃气轮机相同公开(公告)号：US09062885B2
公开(公告)日：2015-06-23
申请号：US13216966
申请日：2011-08-24
申请人： Eiji Takami , Katsunori Tanaka , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Tomo Kawakami , Kei Inoue
发明人： Eiji Takami , Katsunori Tanaka , Koichi Nishida , Shinji Akamatsu , Hideki Haruta , Tomo Kawakami , Kei Inoue
CPC分类号： F23R3/14 , F23R3/28 , F23R3/283 , F23R3/36 , F23R2900/03044
摘要： A fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space.
摘要翻译： 一种用于燃气轮机燃烧器的燃料喷嘴，包括：内筒; 燃烧器筒同心地设置在内圆筒的远端附近的外周上，以包围内筒的前端部; 设置在燃烧器筒和内筒之间用于输送燃烧空气的空气通道; 设置在所述内筒的轴心且在所述内筒的轴向延伸的空间; 多个内通道，其在所述内筒的圆周方向上以相等的间隔设置，用于通过其前端部分喷射流体; 以及至少一个连通部，其设置在所述内筒的前端部的上游侧，并且从所述内筒的外壁向径向内侧延伸，与所述空间连通。
-
公开(公告)号：US20100251718A1
公开(公告)日：2010-10-07
申请号：US12743832
申请日：2008-11-19
CPC分类号： F02C7/24 , F01D25/04 , F23M20/005 , F23R3/26 , F23R2900/00014 , G10K11/161 , G10K11/172
摘要： In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.
摘要翻译： 在根据本发明的阻尼装置中，阻尼装置63安装在旁路管61上，该旁通管61向燃烧器过渡件33供给一定量的高压空气。阻尼装置63包括：流体导入单元71， 通过覆盖旁通管61的外周部分的流体引入空间B，形成共振空间Da和Db的多个声箱73a和73b，其中基部连接到流体引入单元71，并且沿着外部延伸的端部 旁通管61的圆周方向的周向部分以及通过分隔谐振空间Da和Db形成预定长度的共振管道Ea和Eb的隔板74a和74b。
-
28.发明授权Gas turbine combustor having multiple independently operable burners and staging method thereof 有权具有多个可独立操作的燃烧器的燃气轮机燃烧器及其分级方法公开(公告)号：US07797942B2
公开(公告)日：2010-09-21
申请号：US11266202
申请日：2005-11-04
摘要： In a combustor of a gas turbine which has a pilot nozzle being installed to the center of the axis of a combustor basket and a plurality of main nozzles being installed to the vicinity of the pilot nozzle and provided with a premixing tool on the outer circumference thereof, wherein, fuel being injected as air-fuel pre-mixture from the main nozzle into the interior of a transition piece forming a combustion chamber downstream of the combustor basket is ignited by diffusion flame being generated by the pilot nozzle in the transition piece so as to generate a premixed flame in the transition piece, wherein combustion is performed by a part of the plurality of main nozzles from start-up until a predetermined load rate and then performed by adding the remaining portion of the plurality of main nozzles when the predetermined load rate is exceeded.
摘要翻译： 在燃气轮机的燃烧器中，具有安装在燃烧器筐的轴心的中心的先导喷嘴，并且多个主喷嘴安装在导向喷嘴附近，并且在其外周上设置有预混合工具 其特征在于，从所述主喷嘴向所述燃烧器筐下游形成燃烧室的过渡部件的内部喷射的燃料被喷射，所述扩散火焰由所述过渡部件中的先导喷嘴产生， 以在过渡件中产生预混合的火焰，其中燃料由多个主喷嘴的一部分从起动直到预定的负载率进行，然后通过在预定的负载下加入多个主喷嘴的剩余部分 率超过。
-
-
-
-
-
-
-
搜索结果
28 条记录 (耗时 0.023 秒)