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1. 发明申请

US20080184708A1 Gas Turbine Combustor 有权
标题翻译：燃气轮机燃烧器
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。

2. 发明授权

US08408002B2 Gas turbine combustor 有权
标题翻译：燃气轮机燃烧器
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。

3. 发明申请

US20060236700A1 Combustor of gas turbine 有权
标题翻译：燃气轮机燃烧器
公开(公告)号：US20060236700A1
公开(公告)日：2006-10-26
申请号：US11334744
申请日：2006-01-19
申请人： Keijiro Saitoh , Masataka Ohta , Satoshi Tanimura , Shigemi Mandai
发明人： Keijiro Saitoh , Masataka Ohta , Satoshi Tanimura , Shigemi Mandai
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , F23C2900/07001 , Y02E20/344 , Y02T50/675
摘要： A combustor of a gas turbine, which is composed of an inner tube and a transition pipe connected together, comprising: an internal swirler composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring; and an external swirler composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring, the internal swirler and the external swirler being disposed within the inner tube.
摘要翻译：燃气轮机的燃烧器由连接在一起的内管和过渡管构成，包括：内圆筒，其由相对于内管的中心轴线同心设置的圆筒状向内旋流环构成，设置在所述向内旋流器环的外周面上的向内旋流叶片; 以及设置在向内旋流叶片的外周侧并且相对于向内旋流器环同心地形成的圆柱形向外旋流器的外部旋流器，以及设置在向外旋流器环的外周面上的多个向外旋流叶片内部旋流器和外部旋流器设置在内管内。

4. 发明授权

US07669421B2 Combustor of gas turbine with concentric swirler vanes 有权
标题翻译：燃气轮机与同心旋流叶片的燃烧器
公开(公告)号：US07669421B2
公开(公告)日：2010-03-02
申请号：US11334744
申请日：2006-01-19
申请人： Keijiro Saitoh , Masataka Ohta , Satoshi Tanimura , Shigemi Mandai
发明人： Keijiro Saitoh , Masataka Ohta , Satoshi Tanimura , Shigemi Mandai
IPC分类号： F02C3/00
CPC分类号： F23R3/14 , F23C2900/07001 , Y02E20/344 , Y02T50/675
摘要： A gas turbine combustor having an inner tube and a transition pipe connected together is provided. The combustor includes an internal swirler and an external swirler. The internal swirler is composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring. The external swirler is composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring. The internal swirler and the external swirler are disposed within the inner tube.
摘要翻译：提供了具有连接在一起的内管和过渡管的燃气轮机燃烧器。燃烧器包括内部旋流器和外部旋流器。内部旋流器由相对于内管的中心轴线同心设置的圆筒形向内旋流器环以及设置在向内旋流器环的外周表面上的多个向内旋流叶片组成。外部旋流器由设置在向内旋流叶片的外周侧并相对于向内旋流器环同心的圆柱形向外旋流器环组成，并且设置在外旋流器环的外周表面上的多个向外旋流叶片。内部旋流器和外部旋流器设置在内管内。

5. 发明申请

US20100251718A1 DAMPING DEVICE AND GAS TURBINE COMBUSTOR 有权
标题翻译：阻尼装置和燃气轮机
公开(公告)号：US20100251718A1
公开(公告)日：2010-10-07
申请号：US12743832
申请日：2008-11-19
申请人： Takanori Ito , Keisuke Matsuyama , Kazufumi Ikeda , Satoshi Tanimura , Shinji Akamatsu
发明人： Takanori Ito , Keisuke Matsuyama , Kazufumi Ikeda , Satoshi Tanimura , Shinji Akamatsu
IPC分类号： F02C7/24 , F23R3/26
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。

6. 发明授权

US06250065B1 Gas turbine combustion system and combustor ignition method therefor 有权
标题翻译：燃气轮机燃烧系统及燃烧器点火方法
公开(公告)号：US06250065B1
公开(公告)日：2001-06-26
申请号：US09292385
申请日：1999-04-15
申请人： Shigemi Mandai , Tetsuo Gora , Koichi Nishida , Masataka Ota , Ichiro Fukue , Shinji Akamatsu , Satoshi Tanimura , Hideki Haruta , Tomohisa Takasaki , Teruya Tachibana
发明人： Shigemi Mandai , Tetsuo Gora , Koichi Nishida , Masataka Ota , Ichiro Fukue , Shinji Akamatsu , Satoshi Tanimura , Hideki Haruta , Tomohisa Takasaki , Teruya Tachibana
IPC分类号： F02B300
CPC分类号： F02C7/232
摘要： Liquid fuel purge device uses water, not compressed air as in the prior art, thereby prevented are rapid load change of gas turbine due to sudden discharge of liquid fuel and coking of remaining liquid fuel. Upon supply of liquid fuel to fuel nozzle (05) being stopped, water purge system (15) having stop valve (16) supplies water into fuel system including liquid fuel system (08) and fuel nozzle (05) and liquid fuel remaining therein is purged by water into combustion chamber (013) from the fuel nozzle (05).
摘要翻译：液体燃料净化装置如现有技术那样使用水而不是压缩空气，由此防止了由于液体燃料的突然排放和剩余的液体燃料的焦化引起的燃气轮机的快速负荷变化。在向燃料喷嘴（05）停止供应液体燃料时，具有截止阀（16）的净水系统（15）将水供应到包括液体燃料系统（08）和燃料喷嘴（05）的燃料系统中，其中残留的液体燃料是从燃料喷嘴（05）通过水从燃烧室（013）中清除。

7. 发明授权

US08707671B2 Fuel control method and fuel control apparatus for gas turbine and gas turbine 有权
标题翻译：燃气轮机和燃气轮机的燃油控制方法和燃料控制装置
公开(公告)号：US08707671B2
公开(公告)日：2014-04-29
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
IPC分类号： F02C9/32 , F02C9/28 , F23R3/34
CPC分类号： F02C9/26 , F02C9/34 , F05D2270/082 , F23K5/005 , F23R3/286 , F23R3/36
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）点火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。

8. 发明申请

US20110016873A1 FUEL CONTROL METHOD AND FUEL CONTROL APPARATUS FOR GAS TURBINE AND GAS TURBINE 有权
标题翻译：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
IPC分类号： F02C9/26 , F02C7/26
CPC分类号： F02C9/26 , F02C9/34 , F05D2270/082 , F23K5/005 , F23R3/286 , F23R3/36
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。

9. 发明授权

US09291104B2 Damping device and gas turbine combustor 有权
标题翻译：阻尼装置和燃气轮机燃烧器
公开(公告)号：US09291104B2
公开(公告)日：2016-03-22
申请号：US12743832
申请日：2008-11-19
申请人： Takanori Ito , Keisuke Matsuyama , Kazufumi Ikeda , Satoshi Tanimura , Shinji Akamatsu
发明人： Takanori Ito , Keisuke Matsuyama , Kazufumi Ikeda , Satoshi Tanimura , Shinji Akamatsu
IPC分类号： F02C7/24 , F01D25/04 , F23R3/26 , G10K11/172 , F23M20/00 , G10K11/16
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。

10. 发明授权

US6068467A Combustor 有权
标题翻译：燃烧器
公开(公告)号：US6068467A
公开(公告)日：2000-05-30
申请号：US244031
申请日：1999-02-04
申请人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Satoshi Tanimura , Kotaro Miyauchi , Mitsuru Inada , Shinji Akamatsu , Hideki Haruta
发明人： Shigemi Mandai , Koichi Nishida , Masataka Ota , Satoshi Tanimura , Kotaro Miyauchi , Mitsuru Inada , Shinji Akamatsu , Hideki Haruta
IPC分类号： F23D14/02 , F23D23/00 , F23C5/00
CPC分类号： F23D23/00 , F23D14/02 , F23D2206/10 , F23D2209/10 , F23D2900/14021
摘要： A combustor has a pilot nozzle 02 arranged at a central portion of an inner cylinder 01 opening at its end into a combustion chamber 018 and includes a plurality of main nozzles 03 arranged around its outer circumference. Along the outer circumference of a flame holding cone 014 for igniting a fuel F injected from the main nozzles 03 there are disposed elliptical extension pipes 016 of an elliptical sectional shape which are extended from the fronts of the main nozzles 03 to have openings at the axial position of the opening of the flame holding cone 014. As a result, a hot premixed flame 013 does not flow back to a main swirler zone 015 of the circumferential edges of the openings of the main nozzles 03 so that mixing between the fuel F and an air flow A can be improved, reducing the Nox emission while eliminating the burning of a base plate 04 and the main nozzles 03.
摘要翻译：燃烧器具有引导喷嘴02，其设置在内筒01的中心部分处，内筒01在其端部处开放到燃烧室018中，并且包括围绕其外圆周布置的多个主喷嘴03。沿着用于点燃从主喷嘴03喷射的燃料F的火焰保持锥体014的外圆周，设置椭圆形截面形状的椭圆形延伸管016，其从主喷嘴03的前面延伸，以在轴向上具有开口火焰保持锥体014的开口的位置。结果，热预混火焰013不流回到主喷嘴03的开口的周缘的主旋流器区域015，使得燃料F和可以改善空气流A，减少Nox排放，同时消除基板04和主喷嘴03的燃烧。

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